Flight control system and method for an aircraft.

Description

1 / 88 Flight control system and method for an aircraft. Cross-reference to related applications.

[001] This application claims priority to Patent Application No. 18 / 097,035 filed January 13, 2023, entitled FLIGHT CONTROL SYSTEM AND METHOD FOR AN AIRCRAFT, which is a continuation in part of Patent Application No. 17 / 855,376 filed June 30, 2022, which is a continuation of Patent Application No. 17 / 404,614, filed August 17, 2021. Patent Application No. 18 / 097,035 is also a continuation in part of Patent Application No. 17 / 878,006, filed July 31, 2022, which is a continuation of Patent Application No. 17 / 479,828, filed September 20, 2021. The entirety of all of which are incorporated herein in their entirety by way of reference for all purposes. FIELD OF THE INVENTION

[002] The present invention generally relates to the field of flight control. In particular, the present invention is directed to a redundant flight control system and method for an aircraft. BACKGROUND

[003] In aircraft operation, it is essential that all aircraft components remain fully functional for the aircraft to take off, maneuver, and land safely. During some flights, an aircraft component may malfunction or fail, which will put the aircraft in an unsafe mode and compromise the safety of the aircraft, passengers, and cargo on board. SUMMARY OF REVELATION

[004] In one aspect, a flight control system for an aircraft, wherein the flight control system includes a plurality of flight components coupled to an aircraft, wherein the plurality of flight components includes a plurality of redundant control surfaces, a plurality of redundant low-voltage buses connected Petition 870250058780, dated 10 / 07 / 2025, page 7 / 256 2 / 88 communicatively to the plurality of flight components, where a failure in a redundant low-voltage bus of the plurality of redundant low-voltage buses does not affect the operability of the aircraft.

[005] In another aspect, a method of controlling the flight of an aircraft, the method which includes the detection, by a sensor, of the pilot's input from a pilot control, wherein the pilot's input is transmitted to an aircraft flight controller, wherein the aircraft includes a plurality of flight components coupled to an aircraft, wherein the plurality of flight components includes a plurality of redundant control surfaces, and a plurality of redundant low-voltage buses communicatively connected to the plurality of flight components, wherein a failure in a redundant low-voltage bus of the plurality of redundant low-voltage buses does not impact the operability of the aircraft, which generates a failure datum corresponding to a deactivation of a flight component of the plurality of flight components.

[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 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:

[008] Figure 1 is a block diagram illustrating an embodiment of a redundant flight control system configured for use in an aircraft according to aspects of the invention;

[009] Figure 2 is an illustrative embodiment of an electric aircraft;

[010] Figure 3 is a block diagram illustrating an exemplary flight controller according to aspects of the invention; Petition 870250058780, dated 10 / 07 / 2025, p. 8 / 256 3 / 88

[011] Figure 4 is a block diagram illustrating an exemplary machine learning module that can be used to implement any one or more of the methodologies disclosed in this disclosure and any one or more of their portions according to aspects of the invention;

[012] Figure 5 is a flowchart illustrating a method for controlling the flight of an aircraft; and

[013] Figure 6 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.

[014] 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

[015] At a high level, aspects of the present disclosure are directed to systems and methods for redundant flight control configured for use in an aircraft. Aspects of the present disclosure can be used to enable the safe maneuvering of an aircraft during situations where there is a failure of an actuator, flight component, or power source required to control the aircraft's flight to continue and execute the expected flight plan.

[016] In the following description, for explanatory purposes, several specific details are presented to provide a complete understanding of the present invention. It will be evident, however, that the present invention can be practiced without these specific details. As used herein, the word exemplary or illustrative means to serve as an example, instance, or illustration. Any implementation described herein as exemplary or illustrative should not necessarily be interpreted as preferred or advantageous over other implementations. All implementations described below are exemplary implementations provided. Petition 870250058780, dated 10 / 07 / 2025, page 9 / 256 4 / 88 to enable persons skilled in the art to make or use embodiments of the disclosure and are not intended to limit the scope of the disclosure, which is defined by the claims. For purposes of description herein, the terms top, bottom, left, back, right, front, vertical, horizontal and their derivatives shall refer to the invention as set forth in Figure 2. Furthermore, there is no intention to be bound by any theory expressed or implied in the prior technical field, background, brief summary or the detailed description that follows. It should also be understood that the specific devices and processes illustrated in the accompanying drawings, and described in the descriptive report that follows, are simply embodiments of the inventive concepts defined in the appended claims.Therefore, specific dimensions and other physical characteristics related to the modalities disclosed in this document should not be considered limiting, unless the claims expressly state otherwise.

[017] The term communicatively connected, for the purposes of this disclosure, is a process by which a device, component, or circuit is able to receive data and / or transmit data to another device, component, or circuit. Communicative connection may be achieved by wired or wireless electronic communication, directly or through one or more intervening devices or components. In one embodiment, communicative connection includes the electrical connection of an output of one device, component, or circuit to an input of another device, component, or circuit. Communicative connection may be achieved through a bus or other facility for intercommunication between elements of a computing device. Communicative connection may include indirect connections through wireless connection, low-power wide area network, radio communication, optical communication, magnetic, capacitive, or optical connection, or the like.In one embodiment, the communicative connection may include the electrical connection of an output of one device, component, or circuit to an input of another device, component, or circuit. The communicative connection may be performed. Petition 870250058780, dated 10 / 07 / 2025, page 10 / 256 5 / 88 via a bus or other facility for intercommunication between elements of a computing device. The communicative connection may include indirect connections via wireless connection, low-power wide area network, radio communication, optical communication, magnetic, capacitive or optical coupling, or similar.

[018] Aspects of the present revelation allow F. Exemplary modalities that illustrate aspects of the present revelation are described below in the context of several specific examples.

[019] With reference now to Figure 1, an exemplary embodiment of a system 100 for a flight control system 100 for an aircraft 104 is introduced. The aircraft 104 may include an electric aircraft. For the purposes of this disclosure, an electric aircraft is an aircraft that obtains its energy primarily from electricity. The system 100 includes a plurality of flight components 104 attached to the aircraft 104, wherein a movement of the flight component 108 is configured to adjust the attitude of the aircraft 104. A flight component, as described in this disclosure, is any aerodynamic surface attached to an aircraft and interacting with forces to move the aircraft.The flight component 108 may include, as a non-limiting example, ailerons, flaps, leading-edge flaps, rudders, elevators, spoilers, auxiliary airfoils, blades, stabilizers, movable stabilizers, airfoils, a combination thereof, or any other movable surface used to control the aircraft 104 in a fluid medium. The plurality of flight components 108 includes a plurality of redundant control surfaces. A control surface, as used herein, is any flight component, such as ailerons, flaps, leading-edge flaps, rudders, elevators, spoilers, auxiliary airfoils, blades, stabilizers, movable stabilizers, airfoils, a combination thereof, or any other movable surface used to control an aircraft in a fluid medium, thereby affecting flight. The arrangement and composition of the plurality of flight components may result in redundancy. The term. Petition 870250058780, dated 10 / 07 / 2025, page 11 / 256 6 / 88 Redundancy, as used in this disclosure, is the inclusion of components that are not strictly necessary for operation, in the event of failure of other components. For example, redundant control surfaces may include at least two or more ailerons and at least two or more elevators located on each wing of aircraft 104, so that when one of the at least two or more ailerons and / or one of the at least two or more elevators malfunctions, aircraft 104 can still operate correctly.

[020] Referring again to Figure 1, in one or more embodiments, the system 100 may include a plurality of actuators, which includes a first actuator and a second actuator. Each of the first and second actuators may be attached to the flight component 108 and configured to move the flight component. As understood by a person skilled in the art, although the actuators are discussed as a pair of actuators, any number of actuators greater than one may be used to provide redundant flight control of an aircraft 104. In one or more embodiments, the actuators may include pneumatic pistons, hydraulic pistons, and / or solenoid pistons. In other embodiments, the actuators may use electrical components. For example, the actuators may each include a hydraulic piston that extends or retracts to actuate the flight component 108. In another example, the actuators may each include a solenoid.Similarly, actuators can be powered by electrical power, pneumatic pressure, hydraulic pressure, or something similar. Actuators can also include electric motors, servomotors, cables, and the like, as discussed further below.

[021] Still referring to Figure 1, system 100 includes a plurality of redundant low-voltage buses 112 communicatively connected to the plurality of flight components, wherein a failure in one redundant low-voltage bus 112 of the plurality of redundant low-voltage buses 112 does not affect the operability of the aircraft 104. One bus, Petition 870250058780, dated 10 / 07 / 2025, page 12 / 256 7 / 88 as used in this disclosure and in electrical jargon, is any common connection to which any number of loads, which may be connected in parallel and share a relatively similar voltage, may be electrically coupled. A busbar may be responsible for carrying electrical power stored in a battery pack to the plurality of flight components 108 of the aircraft 104. A busbar may be electrically connected to a motor 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. A motor may also include electronic speed controllers or other components for regulating motor speed, direction of rotation, and / or dynamic braking. A battery pack, for the purposes of this disclosure, is an assembly of any number of individual battery modules or identical battery modules.The battery pack may include a plurality of battery cells. The battery pack may include a plurality of electrochemical cells. In a non-limiting embodiment, the battery may be configured to provide electrical power to a plurality of electrical systems of an aircraft 104. In a non-limiting embodiment, each battery in the plurality of batteries may work together to provide electrical power to a plurality of electrical systems of an aircraft 104. For example and without limitation, the battery may be used to power a flight component, a group of flight components, or a set of flight components, as described further below. The battery pack may include a battery management system integrated into the battery pack. For example and without limitation, the battery management system may be consistent with the disclosure of any battery management system in U.S. Serial No. 17 / 104.798 and entitled SYSTEMS AND METHODS FOR A BATTERY MANAGEMENT SYSTEM INTEGRATED IN A BATTERY PACK CONFIGURED FOR USE IN ELECTRIC AIRCRAFT, which is incorporated herein in its entirety by reference. Petition 870250058780, dated 10 / 07 / 2025, page 13 / 256 8 / 88 Those skilled in the art, upon thorough review of this disclosure, will be aware of the various flight components that the battery pack may represent in a manner consistent with this disclosure.

[022] With continued reference to Figure 1, the battery pack may include at least one first pack monitor unit (PMU) and at least one second pack monitor unit. A first pack monitor unit, for the purposes of this disclosure, is a device configured to capture information about a battery. A second pack monitor unit, for the purposes of this disclosure, is a device configured to capture information about a battery. In a non-limiting embodiment, the first PMU and the second PMU may be identical. In a non-limiting embodiment, the second PMU may be configured to detect data after the first PMU. The first pack monitor unit and / or the second pack monitor unit may include a microcontroller. The first pack monitor unit and / or the second pack monitor unit may include a sensor.A sensor, for the purposes of this disclosure, is an electronic device configured to detect, capture, measure, or a combination thereof, a plurality of quantities of external components and electric vehicles. The sensor may be integrated into and / or connected to at least one actuator, a portion thereof, or any subcomponent thereof.

[023] The sensor may include a photodiode configured to convert light, heat, electromagnetic elements and the like into electrical current for further analysis and / or manipulation. The sensor may include electronic circuits or components configured to digitize, transform or otherwise manipulate electrical signals. Electrical signals may include analog signals, digital signals, periodic or aperiodic signals, step signals, unit pulse signal, unit ramp signal, unit parabolic signal, signal function, exponential signal, rectangular signal, triangular signal, sinusoidal signal, sine function, or pulse width modulated signal. The monitor unit of the first package Petition 870250058780, dated 10 / 07 / 2025, page 14 / 256 9 / 88 may include a first set of sensors. The first set of sensors may include a plurality of individual sensors. The monitoring unit of the second package may include a second set of sensors. The second set of sensors may include a plurality of individual sensors. In a non-limiting embodiment, the first set of sensors may be identical to the second set of sensors. The monitoring unit of the first package and / or the monitoring unit of the second package may include a temperature sensor, digital temperature sensor, temperature probe, thermistors, thermocouples, and the like. A temperature sensor, for the purposes of this disclosure, is a device that detects and measures the heat and cold of a battery pack and converts them into electrical signals.The monitoring unit for the first packet and / or the monitoring unit for the second packet may include a controller area network (CAN) isolated transceiver, a pressure sensor, a humidity sensor, an accelerometer, an inertial measurement unit (IMU), a switching regulator, a serial peripheral interface (SPI), and the like. In a non-limiting embodiment, the monitoring unit for the first packet may be identical to the monitoring unit for the second packet. In a non-limiting embodiment, the monitoring unit for the first packet and the monitoring unit for the second packet may be configured to measure identical targets. In a non-limiting embodiment, the monitoring unit for at least the first packet may measure a different datum of a target that at least a second monitoring unit may measure.In a non-limiting embodiment, the monitoring unit of the first battery pack and / or the monitoring unit of the second battery pack may be used to re-verify the datum measurement. In a non-limiting embodiment, the first PMU may be configured to detect the first battery pack datum initially, and the second PMU may be configured to detect a second battery pack datum after a time interval and / or buffer. For example, and without limitation, the second PMU may be configured to start detecting a second battery pack datum. Petition 870250058780, dated 10 / 07 / 2025, page 15 / 256 10 / 88 ten nanoseconds after the first PMU detects the first datum of the battery pack. For example, and without limitation, the second PMU may be configured to begin detecting a second datum of the battery pack sixty seconds after the first PMU detects the first datum of the battery pack. Those skilled in the art, upon reviewing all this disclosure, will be aware of the various detection purposes with a time buffer consistent with this disclosure.

[024] With continued reference to Figure 1, the first PMU may be configured to detect the first battery pack datum. The second PMU is configured to detect a second battery pack datum. A first battery pack datum, for the purposes of this disclosure, is a data element representing the physical attributes of a battery. A second battery pack datum, for the purposes of this disclosure, is a data element representing the physical attributes of a battery. In a non-limiting embodiment, the first battery pack datum and the second battery pack datum may be identical. In a non-limiting embodiment, the second battery pack datum may be detected after the first battery pack datum. The first battery pack datum and / or the second battery pack datum may include an identical information datum. Any datum or signal in this document may include an electrical signal.Electrical signals may include analog signals, digital signals, periodic or aperiodic signals, step signals, unit impulse signals, unit ramp signals, unit parabolic signals, signal functions, exponential signals, rectangular signals, triangular signals, sinusoidal signals, sine functions, or pulse-width modulated signals. The plurality of data captured by the sensor may include a set of circuits, computing devices, electronic components, or a combination thereof that translates into at least one electronic signal configured to be transmitted to another electronic component. First battery reference point and / or second battery reference point may include identification numbers for a battery unit from a plurality of battery units. Petition 870250058780, dated 10 / 07 / 2025, page 16 / 256 11 / 88 In a non-limiting embodiment, the controller may assign the first battery pack datum and / or the second battery pack datum to a unique battery pack unit. The first battery pack datum and / or the second battery pack datum may include information describing, but not limited to, voltage, resistance, current, impedance, distance traveled, and the like. In a non-limiting embodiment, the first battery pack datum may be different from the second battery pack datum. For example, and without limitation, the first battery pack datum may include a voltage of an 800-volt battery, while the second battery pack datum may include a voltage of a 700-volt battery. For example, and without limitation, the first battery pack datum may include a current of a 100 kWh battery pack while the second battery pack datum may include a voltage of an 80 kWh battery pack.The first battery reference point and / or second battery reference point may include a temperature reference point. A temperature datum, for the purposes of this disclosure, is any datum or data element that describes the temperature of a battery pack. The temperature datum may include a heating parameter and a cooling parameter. The heating parameter may include a rate of temperature increase of a battery pack. The cooling parameter may include a rate of temperature decrease of a battery pack. For example, and without limitation, the temperature datum may include a temperature of 15.56 to 26.67 degrees Celsius (60 to 80 degrees Fahrenheit). For example, and without limitation, the cooling parameter may include a battery temperature to be any temperature below 4.44 degrees Celsius (40 degrees Fahrenheit).For example, and without limitation, the heating parameter may include the temperature of a battery being any temperature above 37.78 degrees Celsius (100 degrees Fahrenheit). In the non-limiting embodiment, the temperature datum of the first battery pack may be different from the temperature datum of the second battery pack. For example, e. Petition 870250058780, dated 10 / 07 / 2025, page 17 / 256 12 / 88 without limitation, the temperature datum of the first battery pack may include a battery pack temperature of 21.11 degrees Celsius (70 degrees Fahrenheit) while the datum of the second battery pack may include a battery pack temperature of 37.78 degrees Celsius (100 degrees Fahrenheit). In a non-limiting embodiment, the datum of the first battery pack and / or the datum of the second battery pack may include the total flight hours that the battery pack and / or the aircraft 104 operated. The first battery reference point and / or the second battery reference point may include the total energy that flowed through the battery. The first battery pack datum and / or the second battery pack datum may include a maintenance history of the battery pack. The first battery reference point and / or the second battery reference point may include an upper voltage threshold.The first battery reference point and / or the second battery reference point may include a lower voltage threshold. The first battery reference point and / or the second battery reference point may include a humidity level threshold.

[025] With continued reference to Figure 1, system 100 may include a controller. A controller, for the purposes of this disclosure, is any computing device used to receive and transmit signals. The controller may include a flight controller 128 as described further below. The controller may include a computing device. The computing device may include any computing device as described in this disclosure, including, without limitation, a microcontroller, microprocessor, digital signal processor (DSP), and / or 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 computing device 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. Petition 870250058780, dated 10 / 07 / 2025, page 18 / 256 13 / 88 can be included together in a single computing device or in two or more computing devices, the computing device can interact or communicate with one or more additional devices, as described below in more detail, by means of a network interface device. The network interface device can be used to connect computing devices to one or more networks and to 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, 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. A network may employ a wired and / or wireless communication mode. In general, any network topology can be used. Information (e.g., data, software, etc.)Data can be communicated to and / or from a computer and / or computing device. The computing device 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. The computing device may include one or more computing devices dedicated to data storage, security, traffic distribution for load balancing, and the like. The computing device may distribute one or more computing tasks as described below across a plurality of computing devices, which may operate in parallel, serially, redundantly, or in any other manner used for task or memory distribution among computing devices. Petition 870250058780, dated 10 / 07 / 2025, page 19 / 256 14 / 88 computing can be implemented using a shared-nothing architecture in which data is cached on the worker, in one mode, this can allow for scalability of the 100 system and / or computing device.

[026] With continuous reference to Figure 1, the computing device may 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 computing device may 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 may be performed iteratively and / or recursively using results from previous repetitions as data 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.The computing device may 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 chains, processor cores, or the like; the division of tasks between parallel chains and / or processes may be performed in accordance with any protocol suitable for dividing tasks between iterations. Persons skilled in the art, upon reviewing the entirety of this disclosure, will be aware of the various ways in which steps, sequences of steps, processing tasks, and / or data may be subdivided, shared, or otherwise handled using iteration, recursion, and / or parallel processing.

[027] With continued reference to Figure 1, the first PMU and the second PMU can be configured to transmit the first battery pack datum. Petition 870250058780, dated 10 / 07 / 2025, p. 20 / 256 15 / 88 and the second battery pack datum for the controller. The controller may include any computing device as described in the entirety of this disclosure. In a non-limiting embodiment, the first PMU and the second PMU may transmit battery pack datum plurality based on a plurality of physical controller area network (CAN) bus units. A physical controller area network bus, as used in this disclosure, is a vehicle bus unit that includes a central processing unit (CPU), a CAN controller, and a transceiver designed to allow devices to communicate with each other's applications without the need for a host computer physically located in the aircraft 104.For example, and without limitation, the physical controller area network bus unit may be consistent with the disclosure of any physical controller area network bus unit in U.S. Serial No. 17 / 218,342 entitled "METHOD AND SYSTEM FOR VIRTUALIZING A PLURALITY OF CONTROLLER AREA NETWORK BUS UNITS COMMUNICATIVELY CONNECTED TO AN AIRCRAFT," which is incorporated herein in its entirety by reference. In a non-limiting embodiment, the first PMU may transmit the first battery pack datum to the controller based on a first physical CAN bus unit. In a non-limiting embodiment, the second PMU may transmit the second battery pack datum to the controller based on a second CAN bus unit.Those skilled in the art, upon thorough review of this disclosure, will be aware of the plurality of physical CAN bus units that represent the first CAN bus unit and the second CAN bus unit, as consistent with this disclosure.

[028] With continued reference to Figure 1, system 100 may include a pilot control 116 communicatively connected to a flight controller, wherein the pilot control 116 is configured to transmit at least one pilot input 120 to the flight controller. A pilot control, Petition 870250058780, dated 10 / 07 / 2025, page 21 / 256 16 / 88, as used in this disclosure, is a device used to receive commands from a pilot related to the aircraft. A pilot input, as used herein, is data related to the control or management of an aircraft. Pilot control 116 may be communicatively connected to any other component presented in the system 100. The term communicatively connected, for the purposes of this disclosure, refers to two or more components electrically or otherwise connected and configured to transmit and receive signals from each other. The signals may include electrical, electromagnetic, visual, audio, radio, or other undisclosed types of signals, individually or in combination. The communicative connection may be achieved through a bus or other facility for intercommunication between elements of a computing device.Communicative connections may include indirect connections via wireless, low-power long-distance network, radio communication, optical communication, magnetic, capacitive or optical coupling, or similar. Communicative connections may include redundant connections configured to protect against single-point failure. Pilot control 116 may include a set of circuits, computing devices, electronic components, or a combination thereof that translates pilot input 120 into at least one electronic signal, such as attitude command 124, configured to be transmitted to another electronic component. Pilot control 116 may be a mechanical and / or electrical component that causes actuators and flight components to operate.Pilot control 116 may be physically located in the cockpit of aircraft 104 or located remotely outside aircraft 104 in another location, communicatively connected to at least one portion of aircraft 104. Pilot control 116 may generate and / or transmit an attitude command 124 to flight controller 128 and / or a plurality of flight components. Pilot control 116 may include a pilot interface component. The pilot interface component may be an inceptor stick, collective pitch control, brake pedals, pedal controls, etc. Petition 870250058780, dated 10 / 07 / 2025, page 22 / 256 17 / 88 steering wheel, throttle lever, toggles, steering lever, or control wheel. A person of ordinary skill in the art, upon reading this disclosure in its entirety, would appreciate the variety of input controls that may be present on an aircraft 104 consistent with the present disclosure. The inceptor stick may be consistent with the inceptor stick disclosure in U.S. Serial Application No. 17 / 001,845 entitled A HOVER AND THRUST CONTROL ASSEMBLY FOR DUAL-MODE AIRCRAFT, which is incorporated herein by reference in its entirety. The collective pitch control may be consistent with the collective pitch control disclosure in U.S. Serial Application No. 16 / 929,206 entitled HOVER AND THRUST CONTROL ASSEMBLY FOR DUAL-MODE AIRCRAFT, which is incorporated herein by reference in its entirety.In addition, or alternatively, pilot input 120 may include one or more data sources that provide raw data. “Raw data,” for the purposes of this disclosure, is data representative of aircraft information 104 that has not been conditioned, manipulated, or processed in a manner that renders the data unrepresentative of aircraft information 104. By way of example, pilot input 120 may be provided by a pilot or an automation system. Pilot input 120 may be data from external sensors, data from internal sensors, data retrieved from one or more remote or onboard computing devices. Pilot input 120 may include audiovisual data, pilot voice data, biometric data, or a combination thereof.Pilot 120 input may include raw information or data collected from gyroscopes, inertial measurement units (IMUs), motion sensors, a combination thereof, or other sensors or sensor clusters. Pilot 120 input may include physical manipulation of a control, such as a pilot using their hand and arm to push or pull a lever, or a pilot using a finger to manipulate a switch. Pilot 120 input may also include a pilot's voice command to a microphone and control system. Petition 870250058780, dated 10 / 07 / 2025, page 23 / 256 18 / 88 computation consistent with the entirety of this disclosure.

[029] Referring again to Figure 1, in some embodiments, pilot input 120 may include an attitude command 124. The attitude command 124 may indicate a pilot's desire to change the heading or pitch of an aircraft 104. The term attitude command, for the purposes of this disclosure, refers to at least one data element that identifies a pilot input and / or attitude control. An attitude control, as used herein, is the process of controlling the attitude of an aircraft. The attitude command 124 may describe a transition from fixed-wing flight to rotor-based flight of an aircraft 104, as described further below. The attitude command 124 may indicate a pilot's desire to change the pitch, roll, or yaw of the aircraft. The term pitch, for the purposes of this disclosure, refers to the angle of attack of an aircraft, which is the difference between the nose of the aircraft and the horizontal flight path.For example, an aircraft 104 pitches upward when its nose is tilted upward compared to horizontal flight, as in a climb maneuver. For example, an aircraft 104 pitches downward when its nose is tilted downward compared to horizontal flight, as in a descent maneuver. The term roll, for the purposes of this disclosure, refers to the position of an aircraft around its longitudinal geometric axis, that is, when an aircraft 104 rotates around its geometric axis from tail to nose, and one side rolls upward, as in a bank maneuver. The term yaw, for the purposes of this disclosure, refers to the angle of turn of an aircraft 104, when an aircraft 104 rotates around an imaginary vertical geometric axis that intersects the center of the earth and the fuselage of the aircraft 104. The attitude command 124 may be an electrical signal.Electrical signals can include analog signals, digital signals, periodic or aperiodic signals, step signals, unit impulse signals, unit ramp signals, unit parabolic signals, signal functions, exponential signals, rectangular signals, triangular signals, sinusoidal signals, sine functions, or signals modulated by... Petition 870250058780, dated 10 / 07 / 2025, page 24 / 256 19 / 88 wrist width.

[030] Referring again to Figure 1, in one or more embodiments, pilot control 116 may be controlled by flight controller 128. In another example, pilot control 116 may be a component of flight controller 128. In other embodiments, pilot control 116 may be flight controller 128. The term flight controller, for the purposes of this disclosure, refers to a component or group of components that control the aircraft's trajectory by receiving signals from a pilot and transmitting signals to at least one propeller and other portions of the aircraft, such as flight components, to adjust the trajectory. Flight controller 128 can mix, refine, adjust, redirect, combine, separate, or perform other types of signal operations to translate the pilot's desired trajectory into aircraft maneuvers 104. Flight controller 128, for example, can receive input from pilot 120 to move an input stick from pilot 116's control.The signal for this movement can be sent to flight controller 128, which performs any number or combination of operations on these signals and then sends output signals to any number of aircraft components 104 that work together or independently to maneuver aircraft 104 in response to pilot input 120. Flight controller 128 can condition signals so that they can be sent to and received by multiple components throughout aircraft 104. Flight controller 128 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, flight controller 128 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 a sequence of steps can be performed iteratively and / or recursively using the outputs of previous repetitions as inputs for subsequent repetitions, in order to aggregate inputs and / or outputs of repetitions to produce an aggregate result, reduction or decrease of one or more. Petition 870250058780, dated 10 / 07 / 2025, page 25 / 256 20 / 88 variables, such as global variables, and / or division of a larger processing task into a set of smaller processing tasks addressed iteratively. Flight controller 128 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 chains, processor cores, or the like; task division among parallel chains and / or processes can be performed in accordance with any protocol suitable for task division among iterations. Persons skilled in the art, upon reviewing the entirety of this disclosure, will be 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.Flight controller 128, as well as any other components or combination of components, may be connected to a controller area network (CAN), which can interconnect all components for signal transmission and reception.

[031] Additionally, and with continued reference to Figure 1, flight controller 128 may include and / or communicate with any computing device, including, without limitation, a microcontroller, microprocessor, digital signal processor (DSP), and / or system-on-a-chip (SoC). Flight controller 128 may be programmed to operate aircraft 104 to perform at least one flight maneuver. At least one flight maneuver may include takeoff, landing, stability control maneuvers, emergency response maneuvers, altitude regulation, roll, pitch, yaw, speed, acceleration, or similar maneuvers during any phase of flight. At least one flight maneuver may include a flight plan or sequence of maneuvers to be performed during a flight plan. Flight controller 128 may be designed and configured to operate aircraft 104 through non-mechanical control.Flight controller 128 is communicatively connected to each actuator and thus to each flight component. As a non-limiting example, Petition 870250058780, dated 10 / 07 / 2025, page 26 / 256 21 / 88 Flight controller 128 can transmit signals to the actuators via an electrical circuit connecting flight controller 128 to the actuators. The circuit may include a direct conductive path from flight controller 128 to the actuators or may include an isolated connection, such as an optical or inductive connection. Alternatively, or additionally, flight controller 128 may communicate with the flight using wireless communication, such as, without limitation, communication using electromagnetic radiation, including optical and / or radio communication, or communication via magnetic or capacitive connection.Flight controller 128 may be fully incorporated into aircraft 104 and may be a remote device that operates aircraft 104 remotely via wireless or radio signals, or it may be a combination thereof, such as a computing device in aircraft 104 configured to perform some steps or actions described herein while a remote device is configured to perform other steps. Persons skilled in the art will be aware, after reviewing the entirety of this disclosure, of many different forms and protocols of communication that may be used to communicatively connect flight controller 128 to the actuators.

[032] Referring again to Figure 1, flight controller 128 can interact or communicate with one or more additional devices, as described in more detail below, by means of a network interface device. The network interface device can be used to connect flight controller 128 to one or more networks and to 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 area), a telephone network, a data network associated with a provider of Petition 870250058780, dated 10 / 07 / 2025, page 27 / 256 22 / 88 telephone / voice (e.g., a data and / or voice network from 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 may be used. Information (e.g., data, software, etc.) may be communicated to and / or from a computer and / or computing device. Flight controller 128 may include, but is not limited to, for example, a computing device or grouping of computing devices at a first location and a second computing device or grouping of computing devices at a second location. System 100 may include one or more computing devices dedicated to data storage, security, traffic distribution for load balancing, and the like.Flight controller 128 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. Flight controller 128 can be implemented using a shared-nothing architecture in which data is cached on the worker; in one mode, this can allow for scalability of flight controller 128 and / or computing devices.

[033] Referring again to Figure 1, the system 100 may include a plurality of control assemblies 132. A control assembly, as used in this document, is a set of components related to the flight control of an aircraft. The control assembly 132 may be located on an aircraft wing 104. For example, a control assembly 132 may be a set of flight components, redundant control surfaces, buses, batteries, actuators and the like that work together to produce flight control. The control assembly 132 may be divided into a plurality of component groups. A component group, as Petition 870250058780, dated 10 / 07 / 2025, page 28 / 256 23 / 88 as used in this document, is a group of components used in the flight control of an aircraft that are part of a plurality of redundant components in a control assembly. For example, a group of components may include a single aileron, a single elevator, and a single actuator that work together from a plurality of redundant ailerons, elevators, and actuators located on the same wing of the aircraft 104. An aileron, as used in this document, is a flight control surface used to control the roll of an aircraft. The term elevators, as used in this document, refers to flight control surfaces that control the pitch of the aircraft. In some embodiments, the plurality of redundant control surfaces comprises at least two elevators located on one side of the aircraft.For the purposes of this disclosure, an aircraft side is a portion of an aircraft defined by a vertical plane extending from the aircraft's longitudinal geometric axis. For example, an aircraft may be divided into two sides, one on each side of the aircraft's longitudinal geometric axis. In some embodiments, the aircraft may include one or a plurality of fixed wings attached to both sides of the fuselage, as described further below. A fixed wing, as used in this disclosure, is a wing that derives lift from air movement over aerodynamically designed surfaces that are rigidly and permanently attached to the fuselage. Each group of components may be powered by a separate low-voltage busbar. For example, a first group of components may be connected to a first low-voltage busbar, wherein a second group of components is connected to a second low-voltage busbar.System 100 may include control assembly 132A located on one wing of aircraft 104, and control assembly 132B located on a wing opposite control assembly 132A. Control assembly 132A and control assembly 132B may contain two groups of components for redundancy. For example, and without limitation, control assembly 132A may include a group of... Petition 870250058780, dated 10 / 07 / 2025, page 29 / 256 24 / 88 components 1 and a group of components 2, if an aileron from component group 1 malfunctions, loses communication, or does not operate as intended, this will not affect the flight control of aircraft 104, as the aileron from the competent group 2 may still be fully functional to negate the malfunction of the aileron in group 1. In another example, if a low-voltage bus 112 does not supply power, malfunctions, loses communication, or does not operate as intended in connection with component group 1, this would not affect the flight control of aircraft 104, as the low-voltage bus 112 from component group 2 may still be fully functional to negate the loss of operation of component group 1.Thus, the control assembly 132 can be communicatively connected to receive data from the pilot control 116 so that, if a failure of one group of components is detected, the other group of components will still provide flight control of the aircraft 104. In one or more embodiments, the actuators in a control can receive the attitude command 124 from the pilot control 116 and act simultaneously to move the flight component 108 together. In other embodiments, only one actuator can receive the attitude command 124 to move the flight component. For example, and without limitation, the first actuator can receive the attitude command 124 from the pilot control 116 to move the flight component. Then, if the first actuator fails to move the flight component, the second actuator can move the flight component, as discussed further in this disclosure. The actuators may include components, processors, computing devices, sensors 136, or the like.The actuators may also include a computing device or a plurality of computing devices consistent with the entirety of this disclosure. In one or more embodiments, the pilot control 116 and / or the actuators may communicate with, receive commands from, and / or provide commands to the flight controller 128, as discussed further below.

[034] Referring again to Figure 1, system 100 may include a sensor 136 Petition 870250058780, dated 10 / 07 / 2025, p. 30 / 256 25 / 88 which is communicatively connected to pilot control 116 and to a plurality of actuators. Sensor 136 may be connected to the aircraft 104 or to the actuators, as discussed in the subsequent disclosure. In one or more embodiments, sensor 136 is configured to detect attitude command 124 from pilot control 116, detect the deactivation of a component in a control assembly 132 as described above, and generate a fault datum 140 corresponding to the deactivation. The term fault datum, as used herein, is any datum or data element that describes a fault, abnormality, malfunction, or combination thereof event of an aircraft component. In one or more embodiments, pilot control 116 is configured to receive fault datum 140 from sensor 136 and subsequently generate attitude command 124 to the second actuator to move flight component 108 accordingly.

[035] In one or more modes, sensor 136 may be configured to time all communication between component groups and pilot control 116. Sensor 136 may detect that pilot control 116 has transmitted attitude command 124 to component group 1 and that a flight component 108 has not moved in response to attitude command 124. As a result, sensor 136 may determine that flight component 108 is disabled and thus communicate to pilot control 116 and / or flight controller 128 that flight component 108 in component group 1 is disabled. As a result, flight controller 128 may, for example, alert a pilot about the disabling and transmit a signal to component group 2 for flight control.Although sensor 136 is described as being connected to aircraft 104 and communicating with each competent group, as understood by a person skilled in the art, in other embodiments, an actuator of a component group may include a sensor 136. Sensors 136, as described in this disclosure, are any device, module and / or subsystem that utilizes any hardware, software and / or any combination thereof to detect events and / or changes in the instantaneous environment. Petition 870250058780, dated 10 / 07 / 2025, p. 31 / 256 26 / 88 communicate the information to the vehicle controller. Sensor 136 may be mechanically and / or communicatively connected, as described above, to aircraft 104. Sensor 136 may be configured to detect a fault datum 140. Sensor 136 may be incorporated into aircraft 104 or be remote. The fault datum 140 may include, without limitation, a data element that identifies and / or describes a deactivation of one or more of the plurality of actuators, flight components, buses, motors, battery packs and the like. In one embodiment, sensor 136 may detect that flight component 108 has not moved despite a pilot input 120 on pilot control 116 and thus generate fault datum 140 in response. The fault datum 140 may include, by way of example and without limitation, a determination that a flight component 108 is operating insufficiently, such as, for example, if the first actuator has been damaged or has lost communication.

[036] Referring again to Figure 1, in one or more embodiments, the sensor 136 may include, as an example and without limitation, an environmental sensor 136. As used in this document, an environmental sensor 136 may be used to detect ambient temperature, barometric pressure, air speed, motion sensors 136 which may include gyroscopes, accelerometers, inertial measurement unit (IMU), various magnetics, humidity and / or oxygen. As another non-limiting example, the sensor 136 may include a geospatial sensor 136. As used in this disclosure, a geospatial sensor 136 may include optical / radar / Lidar, GPS, and may be used to detect the location of the aircraft 104, speed of the aircraft 104, altitude of the aircraft 104 and whether the aircraft 104 is in the correct location of the flight plan. Sensor 136 may be located inside aircraft 104. Sensor 136 may be inside a component of aircraft 104.In one embodiment, an environmental sensor 136 can detect one or more environmental conditions or parameters outside the aircraft 104, inside the aircraft 104, or within or on any component thereof, which includes, without limitation, a power source, a propeller, or the like. The environmental sensor 136 can additionally collect... Petition 870250058780, dated 10 / 07 / 2025, page 32 / 256 27 / 88 Environmental information from the predetermined landing site, such as ambient temperature, barometric pressure, airspeed, motion sensors 136 which may include gyroscopes, accelerometers, inertial measurement unit (IMU), various magnetic sensors, humidity and / or oxygen. Information may be collected from external databases and / or information services, such as Aviation Meteorological Information Services. Sensor 136 may detect an environmental parameter, a temperature, a barometric pressure, a location parameter and / or other necessary measurements. Sensor 136 may detect voltage, current or other electrical connection through a direct method or by calculation.This can be accomplished, for example, by using an analog-to-digital converter, one or more comparators, or any other components usable for detecting electrical parameters using an electrical connection, which can be understood by anyone skilled in the art upon full review of this disclosure. Skilled individuals, upon full review of this disclosure, will be aware of various ways to monitor the system status of both critical and non-critical functions.

[037] With continuous reference to Figure 1, flight controller 128 may be configured to receive an electrical parameter related to the plurality of control sets 132, the datum of the first battery pack, the datum of the second battery pack, and other forms of data described throughout this disclosure. As well as, without limitation, flight controller 128 may be configured to receive the fault datum 140 of the sensor actuators 136. The electrical parameter of the actuators is any electrical parameter as described in this disclosure. Flight controller 128 may further be configured to determine, using the electrical parameter, the power-making capacity of the electrical power source. Power-making capacity, as described herein, is the ability to supply power and / or energy to a load or component powered by an electrical power source. A power-making capacity may include Petition 870250058780, dated 10 / 07 / 2025, p. 33 / 256 28 / 88 a power supply capacity. By way of example and without limitation, power supply capacity may include peak power output capacity, average power output capacity, a period of time during which a given power level can be maintained and / or a time at which a given power level can be supplied, including, without limitation, peak and / or average power output capacity. Time is given in terms of a time measurement in seconds and / or other units of a given moment, a time measurement in seconds and / or other units of a given point in a flight plan, or as a given point in a flight plan, such as, without limitation, a time during which power can be supplied may be rendered as a time when an aircraft 104 reaches a given stage in a flight plan.As an example, and without limitation, power output capacity can indicate whether peak power can be supplied in or during a flight landing stage. Power output capacity can include, as a further example and without limitation, power supply capacity, as the total amount of remaining power supplied by a given electrical power source, as well as one or more factors, such as time, temperature, or rate, that can affect the total amount of power available. As a non-limiting example, circumstances that increase the output impedance and / or resistance of an electrical power source and therefore help determine in practical terms how much power can actually be supplied to the components, can be part of the power supply capacity.

[038] Still referring to Figure 1, in some embodiments, flight controller 128 is configured to include an outer loop, an inner loop, and an inverse module. The outer loop may be configured to receive pilot input 120 from sensor 136; generate a rate setpoint as a function of the input reference point of each pilot input 120 of the plurality of pilot inputs 120, where the rate setpoint is the attitude of Petition 870250058780, dated 10 / 07 / 2025, page 34 / 256 29 / 88 roll rate, the desired pitch and yaw rate attitude as determined from each input of the 120 pilot plurality of 120 pilot inputs; and transmit the rate setpoint to the inner loop. The inner loop may be configured to receive the rate setpoint from the outer loop and generate the moment reference point as a function of the rate setpoint. The moment datum may be a data element that identifies and / or describes the moment to be applied to the vehicle. The inner loop may consist of a lead-lag filter for roll rate, yaw rate, and pitch rate, and an integrator that acts only on the yaw rate. The inverse module may be configured to apply a dynamic inverse to each input of the 120 pilot plurality of 120 pilot inputs as a function of the moment datum.The dynamic inverse of each flight component 108 of the plurality of flight components 108 can be applied to drive the flight components.

[039] In one or more embodiments, the sensor 136 may be a plurality of sensors 136 incorporated into the system 100 and / or aircraft 104. The plurality of sensors 136 may be designed to detect a plurality of electrical parameters or environmental data in flight, for example, as described above. The plurality of sensors 136 may, as a non-limiting example, include a voltage sensor 136, wherein the voltage sensor 136 is designed and configured to detect the voltage of one or more power sources of the aircraft 104 and / or actuators. As a further non-limiting example, the plurality of sensors 136 may include a current sensor 136, wherein the current sensor 136 is designed and configured to detect the current of one or more power sources of the aircraft 104 and / or actuators.As another non-limiting example, a plurality of sensors 136 may include a temperature sensor 136, wherein the temperature sensor 136 is designed and configured to detect the temperature of one or more aircraft power sources 104 and / or actuators. As another non-limiting example, a plurality of sensors 136 may include a resistance sensor 136, wherein the resistance sensor 136 is designed and... Petition 870250058780, dated 10 / 07 / 2025, page 35 / 256 30 / 88 configured to detect the resistance of one or more aircraft power sources 104 and / or actuators. As another non-limiting example, a plurality of sensors 136 may include an environmental sensor 136, wherein the environmental sensor 136 may be designed and configured to detect a plurality of environmental data, including, without limitation, ambient air temperature, barometric pressure, turbulence and the like. The environmental sensor 136 may be designed and configured, without limitation, to detect geospatial data to determine the location and altitude of the aircraft 104 by any location method, including, without limitation, GPS, optical, satellite, lidar, radar. The environmental sensor 136, as an example and without limitation, may be designed and configured to detect at least one engine parameter. For example, the environmental sensor 136 may be designed and configured to detect the aircraft engine 104 or the engine of each actuator.Environmental sensor 136 can be designed and configured, without limitation, to detect at least one parameter of the flight components. The sensor datum 136 collected in flight by sensors 136, as described in this disclosure, can be transmitted to flight controller 128 and / or pilot control 116 and can be used to calculate the power output capacity of a power source and / or the projected power requirements of the aircraft 104 during flight.

[040] With reference now to Figure 2, an exemplary embodiment of an aircraft 200 is illustrated. The aircraft 200 may include an electrically powered aircraft. In some embodiments, the electrically powered aircraft may be an electric vertical takeoff and landing (eVTOL) aircraft. The electric aircraft 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. The term rotor-based flight, as described in this disclosure, refers to lift and propulsion generated by the aircraft by means of one or more powered rotors coupled to an engine, such as a quadcopter, multirotor helicopter, or other vehicle that maintains its Petition 870250058780, dated 10 / 07 / 2025, page 36 / 256 31 / 88 lift primarily with the use of downward thrust propellers. The term fixed-wing flight, as described in this disclosure, is where the aircraft is capable of flying 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, like airplane flight.

[041] Referring again to Figure 2, aircraft 200 may include control assembly 132 A and control assembly 132 B on either wing of aircraft 200. In some embodiments, the aircraft may include control assembly 132 A and control assembly 132 B on the tail of the aircraft. Aircraft 200 may include a fuselage 204. As used in this disclosure, a fuselage is the main body of an aircraft, or in other words, the entirety of the aircraft except the cockpit, nose, wings, empennage, nacelles, any and all control surfaces, and generally contains the payload of an aircraft. The fuselage 204 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 204 fuselage may include a truss structure. A truss structure may be used with a lightweight aircraft and may include welded steel tube trusses. A truss, as used herein, 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. Petition 870250058780, dated 10 / 07 / 2025, page 37 / 256 32 / 88 will be discussed in more detail later in this document.

[042] Referring again to Figure 2, the aircraft 200 may include a plurality of actuators 208. In one embodiment, the actuator 102 may be mechanically coupled to an aircraft. 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 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 used in this disclosure, an aircraft is a vehicle that can fly. As a non-limiting example, aircraft may include airplanes, helicopters, aerostats, airships, gliders, paramotors, and the like.In one embodiment, the mechanical coupling can be used to connect the ends of adjacent parts and / or objects of an electric aircraft. Additionally, in another embodiment, the mechanical coupling can be used to join two parts of rotating components of electric aircraft.

[043] With continued reference to Figure 2, a plurality of actuators 208 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. Petition 870250058780, dated 10 / 07 / 2025, page 38 / 256 33 / 88 and / or thrust. For example, the plurality of actuators 208 may include a component used to produce a torque that affects the 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 208 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 208 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 200.The plurality of actuators 208 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.

[044] Referring again to Figure 2, a plurality of actuators 208 may include at least one propulsion component. As used in this disclosure, a propulsion component 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 may simultaneously push 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. In one embodiment, the propulsion component may include an extractor component.As used in this disclosure, a traction component is a component that pulls and / or... Petition 870250058780, dated 10 / 07 / 2025, page 39 / 256 34 / 88 tows an aircraft through a medium. As a non-limiting example, the extractor component may include a flight component, such as an extractor propeller, an extractor engine, an extractor propeller, and the like. Furthermore, or alternatively, the extractor component may include a plurality of extractor flight components. In another embodiment, the propulsion component may include a pusher component. As used in this disclosure, a pusher component is a component that pushes and / or produces thrust on an aircraft through a medium. As a non-limiting example, the propulsion component may include a propulsion component, such as an pusher propeller, an extractor engine, an extractor propeller, and the like. Furthermore, or alternatively, the pusher flight component may include a plurality of pusher flight components.

[045] In another embodiment, and still referring to Figure 2, 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 push the propeller forward or backward. The propeller may include a power-driven rotating hub to which several radial airfoil section blades may be attached, such 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 document. 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 could be an angle of 2.2° inward and / or 1.7° forward. As another non-limiting example, a fixed angle could be an angle of 7.6° 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. Petition 870250058780, dated 10 / 07 / 2025, page 40 / 256 35 / 88 similar to the thread of a screw that makes an angle with the shaft; this angle can be referred to as a pitch or pitch angle which will determine a forward speed of movement as the blade rotates. Additionally, 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 7.3° inward, whereupon the propeller component may be rotated and / or shifted to a second angle of 1.7° outward.

[046] Referring again to Figure 2, 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.

[047] With continued reference to Figure 2, the plurality of actuators 208 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 208 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 a motor drive, such as, without limitation, a 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 drive may include an inverter. A motor drive may also include controllers Petition 870250058780, dated 10 / 07 / 2025, page 41 / 256 36 / 88 electronic speed controllers, inverters or other components for regulating motor speed, direction of rotation and / or dynamic braking.

[048] Referring again to Figure 2, a plurality of actuators 208 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 plurality of battery cells connected in series in a module and each module connected in series or in parallel with other modules. The power source may include a battery pack. The configuration of a power source 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 in which the system may be incorporated.

[049] In one embodiment, and still referring to Figure 2, a power source may be used to provide a constant supply of electrical power to a load during a flight by an electric aircraft 200. For example, the power source may be able to provide sufficient power for cruise and other relatively low-power flight phases. A power source may also be able to provide electrical power for some higher-power flight phases, particularly when the power source is at a high SOC, as may be the case, for example, during takeoff. In one embodiment, the power source may include an emergency power unit that may be able to provide sufficient electrical power for auxiliary loads, which includes, without limitation, lighting, navigation, communications, de-icing, steering, or other systems that require power or energy.Furthermore, the power source may be able to provide sufficient power for controlled descent and landing protocols, including, but not limited to... Petition 870250058780, dated 10 / 07 / 2025, page 42 / 256 37 / 88 limitation, hovering descent or runway landing. As used in this document, the power source may have high power density, where the electrical power that a power source 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 source 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 source include batteries used for starting applications which include lithium-ion batteries which may include NCA, NMC, lithium iron phosphate (LiFePO2) and lithium manganese oxide (LMO) batteries,which can 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 or titanite anode, the power source can 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 iron phosphate (LiFePO2), 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 which, Petition 870250058780, dated 10 / 07 / 2025, p. 43 / 256 38 / 88 can be used as a power source.

[050] Referring again to Figure 2, a power source may include a plurality of power sources, herein referred to 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 high peak load is needed. 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 from at least one power source 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 source 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.Persons 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 / 922,157 and No. 16 / 022,120, both entitled SYSTEM AND METHOD FOR HIGH ENERGY DENSITY BATTERY MODULE by S. Donovan et al., which are incorporated herein in their entirety. Petition 870250058780, dated 10 / 07 / 2025, page 44 / 256 39 / 88 total for reference purposes.

[051] Referring again to Figure 2, according to some embodiments, a power source may include an emergency power unit (EPU) (i.e., auxiliary power unit). As used in this disclosure, an emergency power unit is a power source 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 source has failed, is depleted, or is unavailable. Non-limiting exemplary essential systems include navigation systems such as MFD, GPS, VOR receiver or directional gyroscope and other essential flight components such as thrusters.

[052] Referring again to Figure 2, 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 200 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.

[053] Referring again to Figure 2, aircraft 200 may include a pilot control 212, 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 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 208. 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, pilot control 212 may include a throttle 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 throttle control may alter and / or adjust the roll angle of aircraft 200 as a function of the control and / or Petition 870250058780, dated 10 / 07 / 2025, page 45 / 25640 / 88 Aileron maneuver. In one embodiment, pilot control 212 may include one or more foot brakes, control stick, pedals, throttle levels, and the like. In another embodiment, and without limitation, pilot control 212 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, 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 yaw geometric axis is a geometric axis directed toward the underside of the aircraft, perpendicular to the wings. For example, and without limitation, a positive yaw movement may include the adjustment and / or displacement of the aircraft's nose 200 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 200 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 roll motion may include raising the left wing and lowering the right wing simultaneously.

[054] Still referring to Figure 2, the pilot control 212 can be configured to modify a variable pitch angle. For example, and without limitation, the pilot control 212 can 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 can include a propeller blade pitched at 7.2°. In one embodiment, the pilot control 212 can modify the variable pitch angle from a first angle of 2.71° to a second angle of 7.22°. In addition Petition 870250058780, dated 10 / 07 / 2025, page 46 / 256 41 / 88 of this, or alternatively, the pilot control 212 may be configured to translate a desired torque from the pilot to the actuator 208. For example, and without limitation, the pilot control 212 may translate that the desired torque from a pilot to a propeller is 160 lb. ft. of torque. As another non-limiting example, the pilot control 212 may introduce the desired torque from the pilot so that a propeller has 290 lb. ft. of torque. Further disclosure relating to the pilot control 212 may be found in U.S. Patent Applications No. 17 / 001,225 and U.S. 16 / 929,206, both entitled A HOVER AND THRUST CONTROL ASSEMBLY FOR DUAL-MODE AIRCRAFT by C. Spiegel et al., which are incorporated herein in their entirety by reference.

[055] Referring again to Figure 2, aircraft 200 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 aircraft 200 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 727. Further disclosure relating to loading systems may be found in U.S. Patent Application No. 17 / 137,592 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.

[056] Referring again to Figure 2, aircraft 200 may include a sensor 216. Sensor 216 may be configured to detect a characteristic of pilot control 212. The sensor may be a device, module and / or subsystem that 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 212 to which the sensor is near or otherwise detected in a communication. Petition 870250058780, dated 10 / 07 / 2025, p. 47 / 256 42 / 88 and transmit information associated with the feature, for example, without limitation, digitized data. Sensor 216 may be mechanically and / or communicatively coupled to the aircraft 200, including, for example, at least one control pilot 212. Sensor 216 may be configured to detect a feature associated with at least one pilot control 212. An environmental sensor may include, without limitation, one or more sensors used to detect ambient temperature, barometric pressure and / or airspeed, one or more motion sensors which may include, without 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 216 may include at least one geospatial sensor. Sensor 216 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 status of the aircraft for both critical and non-critical functions. The sensor may be embedded in the vehicle or aircraft or be remote.

[057] Referring again to Figure 2, in some embodiments, sensor 216 may be configured to detect a feature associated with any pilot control described in this disclosure. Non-limiting examples of a sensor 216 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 216 may detect a feature as an analog measurement, for example, which yields a continuously varying electrical potential indicative of the detected feature. In such cases, sensor 216 may additionally comprise an analog-to-digital converter (ADC), as well as any additional circuitry such as, without limitation, a Wheatstone bridge, a Petition 870250058780, dated 10 / 07 / 2025, p. 48 / 256 43 / 88 amplifier, a filter and the like. For example, in some cases, sensor 216 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 may then digitize the analog signal and produce a digital signal that may be transmitted to other systems within the aircraft 200, for example, without limitation, a computing system, a pilot display and a memory component. Alternatively or additionally, sensor 216 may detect a characteristic of a pilot control 212 digitally.For example, in some embodiments, the 216 sensor may detect a feature digitally or digitize a natively detected signal. In some cases, for example, the 216 sensor 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.

[058] Referring again to Figure 2, the electric aircraft 200 may include at least one motor, which may be mounted on a structural feature of the aircraft. The motor design 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 by requiring fewer large holes in the mounting area. In some embodiments, the motor 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 200 component. For example, and without limitation, the structural feature may be any portion of a vehicle that incorporates Petition 870250058780, dated 10 / 07 / 2025, page 49 / 256 44 / 88 engine, 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 portion 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, which includes, without limitation, metal 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 one actuator 202. 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.

[059] Referring again to Figure 2, the electric aircraft 200 may include an eVTOL (eVertical Takeoff and Landing) aircraft. As used in this disclosure, an eVTOL is one that can hover, take off, and land vertically. An eVTOL, as used in this document, is an electrically powered aircraft that typically uses one power source from a plurality of power sources to power the aircraft. In order to optimize the power and energy required to propel the aircraft, the eVTOL 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 document, is where the aircraft has generated lift and propulsion by means of one or more powered rotors coupled to a motor, such as a Petition 870250058780, dated 10 / 07 / 2025, page 50 / 256 45 / 88 quadcopter, multirotor helicopter or other vehicle that maintains its lift primarily through the use of downward thrust propellers. The term fixed-wing flight, as described in this document, 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.

[060] With continued reference to Figure 2, various aerodynamic forces can act on the Electric Aircraft 200 during flight. The forces acting on the Electric Aircraft 200 during flight may include, without limitation, thrust, the forward force produced by the rotating element of the Electric Aircraft 200 and acting parallel to the longitudinal geometric axis. Another force acting on the Electric Aircraft 200 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 200, 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 200 may include, without limitation, weight, which may include a combined load of the Electric Aircraft 200 itself, crew, baggage, and / or fuel.Weight can pull electric 200 aircraft downwards due to the force of gravity. An additional force acting on electric 200 aircraft 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 actuator 208. 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, electric 200 aircraft are designed to be as light as possible. Reducing the weight of the aircraft and designing to reduce the number of components is essential to optimize weight. To save energy, it may be useful to reduce the weight of the components of electric 200 aircraft, which includes, but is not limited to... Petition 870250058780, dated 10 / 07 / 2025, page 51 / 256 46 / 88 limitation, propellers and / or propulsion systems. In one embodiment, the motor can eliminate the need for many external structural features that might otherwise be required to join one component to another. The 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 electric aircraft 200 and / or propellers.

[061] With continued reference to Figure 2, in some embodiments, electric aircraft 200 may include a flight controller 220. The flight controller 220 may be consistent with any flight controller disclosed in this disclosure.

[062] Now, referring to Figure 3, an exemplary embodiment of the flight controller 132 is illustrated. The flight controller 132 may include and / or communicate with any computing device as described in this disclosure, including, without limitation, a microcontroller, microprocessor, digital signal processor (DSP), and / or system-on-a-chip (SoC) as described in this disclosure.Furthermore, flight controller 132 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. In embodiments, flight controller 304 may be installed in an aircraft, may control the aircraft remotely, and / or may include an element installed in the aircraft and a remote element communicating with it.

[063] In one embodiment, and still referring to Figure 3, flight controller 128 may include a signal transformation component 308. As used in this disclosure, a signal transformation component is a component that transforms and / or converts a first signal into a second signal, wherein a signal may include one or more digital and / or analog signals. For example, and Petition 870250058780, dated 10 / 07 / 2025, page 52 / 256 47 / 88 without limitation, the 308 signal transformation component may be configured to perform one or more operations, such as preprocessing, lexical analysis, parsing, semantic analysis, and the like. In one embodiment, and without limitation, the 308 signal transformation component may include one or more analog-to-digital converters that transform a first signal from an analog signal into a second signal from a digital signal. For example, and without limitation, an analog-to-digital converter may convert an analog input signal into a 10-bit binary digital representation of that signal. In another embodiment, the 308 signal transformation component may include the transformation of one or more low-level languages, such as, but not limited to, machine languages ​​and / or assembly languages. For example, and without limitation, the 308 signal transformation component may include the transformation of a binary language signal into an assembly language signal.In one embodiment, and without limitation, the signal transformation component 308 may include the transformation of one or more high-level languages ​​and / or formal languages, such as, but not limited to, alphabets, strings, and / or languages. For example, and without limitation, high-level languages ​​may include one or more system languages, scripting languages, domain-specific languages, visual languages, esoteric languages, and the like. As another non-limiting example, high-level languages ​​may include one or more algebraic formula languages, business data languages, string and list languages, object-oriented languages, and the like.

[064] Referring again to Figure 3, the signal transformation component 308 can be configured to optimize an intermediate representation 312. As used in this disclosure, an intermediate representation is a data structure and / or code that represents the input signal. The signal transformation component 308 can optimize the intermediate representation based on data flow analysis, dependency analysis, alias analysis, pointer analysis, escape analysis, and the like. In a Petition 870250058780, dated 10 / 07 / 2025, page 53 / 256 In one embodiment, and without limitation, the signal transformation component 308 can optimize the intermediate representation 312 based on one or more inline expansions, dead code eliminations, constant propagation, loop transformations, and / or automatic parallelization functions. In another embodiment, the signal transformation component 308 can optimize the intermediate representation based on a machine-dependent optimization, such as a magic eye optimization, wherein a magic eye optimization can rewrite short code sequences into more efficient code sequences. The signal transformation component 308 can optimize the intermediate representation to generate an output language, wherein an output language, as used herein, is the native machine language of the flight controller 128. For example, and without limitation, the native machine language may include one or more binary and / or numeric languages.

[065] In one embodiment, and without limitation, the signal transformation component 308 may include the transformation of one or more inputs and outputs as a function of an error correction code. An error correction code, also known as an error correction code (ECC), is an encoding of a message or batch of data using redundant information, which allows the recovery of corrupted data. An ECC may include a block code, in which information is encoded in fixed-size packets and / or blocks of data elements, such as symbols of predetermined size, bits, or the like.Reed-Solomon encoding, in which the message symbols within a set of symbols with q symbols are encoded as coefficients of a polynomial of degree less than or equal to a natural number k, over a finite field F with q elements; the strings thus encoded have a minimum Hamming distance of k+1, and allow the correction of (qk-1) / 2 erroneous symbols. The block code can alternatively or additionally be implemented using Golay encoding, also known as binary Golay encoding, Bose encoding. 49 / 88 Chaudhuri coding, Hocquenghuem coding (BCH), multidimensional parity check coding and / or Hamming codes. An ECC may alternatively or additionally be based on a convolutional code.

[066] In one embodiment, and still referring to Figure 3, the flight controller 128 may include a reconfigurable hardware platform 316. A reconfigurable hardware platform, as used in this document, is a hardware component and / or unit that can be reprogrammed, so that, for example, a data path between elements such as logic gates or other digital circuit elements can be modified to alter an algorithm, state, logical sequence or similar of the component and / or unit. This can be done with flexible high-speed computing meshes, such as field-programmable gate arrays (FPGAs), which may include a grid of interconnected logic gates, connections between which can be cut and / or restored to program in modified logic.The 316 reconfigurable hardware platform can be reconfigured to implement any algorithm and / or algorithm selection process received from another computing device and / or created using machine learning processes.

[067] Referring again to Figure 3, the reconfigurable hardware platform 316 may include a logic component 320. As used in this disclosure, a logic component is a component that executes instructions in the output language. For example, and without limitation, the logic component may perform basic arithmetic, logic, control, input / output, and similar operations. The logic component 320 may include any suitable processor, such as, without limitation, a component incorporating logic circuits to perform arithmetic and logic 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 logic component 320 may be organized according to the Von Neumann and / or Harvard architecture as a non-limiting example. The logic component 320 may include, Petition 870250058780, dated 10 / 07 / 2025, page 55 / 256 50 / 88 to 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). In one embodiment, the logic component 320 may include one or more integrated circuit microprocessors, which may contain one or more central processing units, central processors, and / or main processors, on a single metal-oxide-semiconductor chip. The logic component 320 may be configured to execute a sequence of stored instructions to be executed in the output language and / or intermediate representation 312.Logic component 320 may be configured to fetch and / or retrieve the instruction from a memory cache, wherein a memory cache, as used in this disclosure, is a set of instructions stored in flight controller 128. Logic component 320 may be configured to decode the instruction retrieved from the memory cache into opcodes and / or operands. Logic component 320 may be configured to execute the instruction in intermediate representation 312 and / or output language. For example, and without limitation, logic component 320 may be configured to perform an addition operation in intermediate representation 312 and / or output language.

[068] In one embodiment, and without limitation, logical component 320 may be configured to compute a flight element 324. As used in this disclosure, a flight element is a datum element that denotes a relative state of the aircraft. For example, and without limitation, flight element 324 may denote one or more torques, thrusts, airspeed speeds, forces, altitudes, ground speeds, directions during flight, facing directions, forces, orientations, and the like thereof. For example, and without limitation, flight element 324 may denote that the aircraft is navigating Petition 870250058780, dated 10 / 07 / 2025, page 56 / 256 51 / 88 at a sufficient altitude and / or magnitude of forward thrust. As another non-limiting example, the flight state may denote that it is accumulating thrust and / or speed of travel in preparation for takeoff. As another non-limiting example, flight element 324 may denote that the aircraft is following a flight path accurately and / or sufficiently.

[069] Referring again to Figure 3, flight controller 128 may include a chipset component 328. As used in this disclosure, a chipset component is a component that manages data flow. In one embodiment, and without limitation, the chipset component 328 may include a northbridge data flow path, wherein the northbridge data flow path may manage data flow from logic component 320 to a high-speed device and / or component, such as RAM, graphics controller, and the like. In another embodiment, and without limitation, the chipset component 328 may include a southbridge data flow path, wherein the southbridge data flow path may manage data flow from logic component 320 to lower-speed peripheral buses, such as a peripheral component interconnect (PCI), industry standard architecture (ICA), and the like.In one embodiment, and without limitation, the southbridge data flow path may include managing data flow between peripheral connections such as Ethernet, USB, audio devices, and the like. Additionally, or alternatively, component 328 of the chipset may manage data flow between logic component 320, the memory cache, and a flight component 332. As used in this disclosure, a flight component is a portion of an aircraft that can be moved or adjusted to affect one or more flight elements. For example, flight component 332 may include a component used to affect the roll and pitch of the aircraft, which may include one or more ailerons. As another example, flight component 332 may include a rudder to control the yaw of an aircraft. Petition 870250058780, dated 10 / 07 / 2025, page 57 / 256 52 / 88 aircraft. In one embodiment, the chipset component 328 may be configured to communicate with a plurality of flight components based on flight element 324. For example, and without limitation, the chipset component 328 may transmit to an aircraft rotor to reduce the torque of a first-lift propeller and increase the forward thrust produced by a pusher component to perform a flight maneuver.

[070] In one embodiment, and still referring to Figure 3, flight controller 128 may be configured to generate an autonomous function. As used in this disclosure, an autonomous function is a mode and / or function of flight controller 128 that controls the aircraft automatically. For example, and without limitation, the autonomous function may perform one or more aircraft maneuvers, takeoffs, landings, altitude adjustments, flight leveling adjustments, turns, climbs and / or descents. As another non-limiting example, the autonomous function may adjust one or more airspeed, thrust, torque and / or ground speed. As another non-limiting example, the autonomous function may perform one or more flight path corrections and / or flight path modifications based on flight element 324. In one embodiment, the autonomous function may include one or more autonomy modes, such as, but not limited to, autonomous mode, semi-autonomous mode and / or non-autonomous mode.As used in this disclosure, autonomous mode is a mode that automatically adjusts and / or controls the aircraft and / or aircraft maneuvers in their entirety. For example, autonomous mode may denote that flight controller 128 will adjust the aircraft. As used in this disclosure, a semi-autonomous mode is a mode that automatically adjusts and / or controls a portion and / or section of the aircraft. For example, and without limitation, semi-autonomous mode may denote that a pilot will control the propellers, wherein flight controller 128 will control the ailerons and / or rudders. As used in this disclosure, non-autonomous mode is a mode that denotes that a pilot will control the aircraft and / or its maneuvers. Petition 870250058780, dated 10 / 07 / 2025, page 58 / 256 53 / 88 aircraft in total.

[071] In one embodiment, and still referring to Figure 3, flight controller 128 can generate autonomous function based on an autonomous machine learning model. As used in this disclosure, an autonomous machine learning model is a machine learning model to produce an autonomous function output given flight element 324 and a pilot signal 336 as inputs; this contrasts with a non-machine learning software program, where the commands to be executed are predetermined by a user and written in a programming language. As used in this disclosure, a pilot signal is a datum element that represents one or more functions that a pilot controls and / or adjusts. For example, pilot signal 336 might denote that a pilot is controlling and / or maneuvering ailerons, where the pilot is not in control of rudders and / or propellers.In one embodiment, pilot signal 336 may include an implicit signal and / or an explicit signal. For example, and without limitation, pilot signal 336 may include an explicit signal where the pilot explicitly states that there is a lack of control and / or a desire for autonomous operation. As a further non-limiting example, pilot signal 336 may include an explicit signal directing flight controller 128 to control and / or maintain a portion of the aircraft, a portion of the flight plan, the entire aircraft, and / or the entire flight plan. As another non-limiting example, pilot signal 336 may include an implicit signal where flight controller 128 detects a lack of control, such as malfunction, torque alteration, deviation from the flight path, and the like.In one embodiment, and without limitation, the pilot signal 336 may include one or more explicit signals to reduce torque and / or one or more implicit signals that torque may be reduced due to a reduction in airspeed. In one embodiment, and without limitation, the pilot signal 336 may include one or more local and / or global signals. For example, and without limitation, the pilot signal 336 may include a local signal that is transmitted by a pilot and / or crew member. As another non-limiting example, the pilot signal... Petition 870250058780, dated 10 / 07 / 2025, page 59 / 256 54 / 88 336 may include a global signal that is transmitted by air traffic control and / or one or more remote users who are in communication with the aircraft pilot. In one embodiment, the 336 pilot signal may be received via a three-state bus and / or multiplexer, which indicates that an explicit pilot signal must be transmitted before any implicit or global pilot signal.

[072] Referring again to Figure 3, the autonomous machine learning model may include one or more autonomous machine learning processes, such as supervised, unsupervised, or reinforcement machine learning processes that flight controller 128 and / or a remote device may or may not use in autonomous function generation. As used in this disclosure, a remote device is a device external to flight controller 128. Additionally, or alternatively, the autonomous machine learning model may include one or more autonomous machine learning processes that an FPGA (field-programmable gate array) may or may not use in autonomous function generation.The autonomous machine learning process may include, without limitation, machine learning processes such as simple linear regression, multiple linear regression, polynomial regression, support vector regression, ridge regression, lasso regression, elasticnet regression, decision tree regression, random forest regression, logistic regression, logistic classification, K nearest neighbors, support vector machines, kernel support vector machines, naive bayes, decision tree classification, random forest classification, K-means clustering, hierarchical clustering, dimensionality reduction, principal component analysis, linear discriminant analysis, kernel principal component analysis, Q learning, State Action Reward State Action (SARSA), Deep Q network, Markov decision processes, Deep Deterministic Policy Gradient (DDPG) or similar.

[073] In one embodiment, and still referring to Figure 3, the model of Petition 870250058780, dated 10 / 07 / 2025, p. 60 / 256 55 / 88 Autonomous machine learning can be trained based on autonomous training data, wherein the autonomous training data can correlate a flight element, pilot signal, and / or simulation data to an autonomous function. For example, and without limitation, a flight element of an airspeed, a pilot signal of limited and / or no thrust control, and simulation data of the airspeed required to reach the destination can result in an autonomous function that includes a semi-autonomous mode to increase thrust. The autonomous training data can be received based on user-entered evaluations of flight elements, pilot signals, simulation data, and / or autonomous functions.Flight controller 128 can receive autonomous training data by receiving flight element, pilot signal, and / or simulation data correlations with an autonomous function that were previously received and / or determined during a previous autonomous function generation iteration. Autonomous training data can be received by one or more remote devices and / or FPGAs that at least correlate a flight element, pilot signal, and / or simulation data to an autonomous function. Autonomous training data can be received in the form of one or more user-entered correlations of a flight element, pilot signal, and / or simulation data to an autonomous function.

[074] Referring again to Figure 3, flight controller 128 can receive an autonomous machine learning model from a remote device and / or FPGA that uses one or more autonomous machine learning processes, wherein a remote device and an FPGA are described above in detail. For example, and without limitation, a remote device may include a computing device, external device, processor, FPGA, microprocessor, and the like. The remote device and / or FPGA can execute the autonomous machine learning process using autonomous training data to generate autonomous functions and transmit the output to flight controller 128. The remote device and / or FPGA can transmit a signal, bit, datum, or Petition 870250058780, dated 10 / 07 / 2025, page 61 / 256 56 / 88 parameter for flight controller 128 that at least relates to the autonomous function. Additionally, or alternatively, the remote device and / or FPGA may provide an updated machine learning model. For example, and without limitation, an updated machine learning model may consist of a firmware update, a software update, an autonomous machine learning process correction, and the like. As a non-limiting example, a software update may incorporate new simulation data related to a modified flight element.Furthermore, or alternatively, the updated machine learning model can be transmitted to the remote device and / or FPGA, where the remote device and / or FPGA can replace the autonomous machine learning model with the updated machine learning model and generate the autonomous function as a function of the flight element, pilot signal, and / or simulation data using the updated machine learning model. The updated machine learning model can be transmitted by the remote device and / or FPGA and received by the flight controller as a software update, firmware update, or corrected autonomous machine learning model. For example, and without limitation, the autonomous machine learning model can utilize a neural network machine learning process, where the updated machine learning model can incorporate a gradient boosting machine learning process.

[075] Referring again to Figure 3, flight controller 128 can include, be included in, and / or communicate with a mobile device, such as a cell phone or smartphone. Additionally, the flight controller can communicate with one or more additional devices, as described in more detail below, through a network interface device. The network interface device can be used to commutatively connect a flight controller to one or more of a variety of networks and one or more devices. Examples of a network interface device include, however, Petition 870250058780, dated 10 / 07 / 2025, p. 62 / 256 57 / 88 without limitation, 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 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. The network may include any network topology and may employ a wired and / or wireless communication mode.

[076] In one embodiment, and still referring to Figure 3, flight controller 128 may include, but is not limited to, for example, a grouping of flight controllers at a first location and a second flight controller or grouping of flight controllers at a second location. Flight controller 128 may include one or more flight controllers dedicated to data storage, safety, traffic distribution for load balancing, and the like. Flight controller 128 may be configured to distribute one or more computing tasks as described below across a plurality of flight controllers, which may operate in parallel, in series, redundantly, or in any other manner used for task or memory distribution among computing devices. For example, and without limitation, flight controller 128 may implement a control algorithm to distribute and / or command the plurality of flight controllers.As used in this disclosure, a control algorithm is a finite sequence of well-defined, computer-implementable instructions that can determine the flight component from a plurality of flight components to be adjusted. For example, and without limitation, the control algorithm may include one or more algorithms that reduce and / or avoid aviation asymmetry. As another non-limiting example, algorithms... Petition 870250058780, dated 10 / 07 / 2025, page 63 / 256 58 / 88 control algorithms may include one or more models generated based on software, including, but not limited to, Simulink from MathWorks, Natick, Massachusetts, USA. In one embodiment, and without limitation, the control algorithm may be configured to generate automatic code, wherein automatic code as used herein is code and / or an algorithm generated based on one or more models and / or software. In another embodiment, the control algorithm may be configured to produce a segmented control algorithm. As used in this disclosure, a segmented control algorithm is a control algorithm that has been separated and / or analyzed into discrete sections. For example, and without limitation, the segmented control algorithm may analyze the control algorithm into two or more segments, wherein each segment of the control algorithm may be executed by one or more flight controllers operating on distinct flight components.

[077] In one embodiment, and still referring to Figure 3, the control algorithm may be configured to determine a segmentation contour as a function of the segmented control algorithm. As used in this disclosure, a segmentation contour is a boundary and / or delineation associated with the segments of the segmented control algorithm. For example, and without limitation, the segmentation contour may denote that a segment in the control algorithm has a first start section and / or a first end section. As another non-limiting example, the segmentation contour may include one or more contours associated with a flight component capability 332. In one embodiment, the control algorithm may be configured to create an optimized signal communication as a function of the segmentation contour.For example, and without limitation, optimized signal communication may include identifying the discrete time required to transmit and / or receive one or more segmentation contours. In one embodiment, and without limitation, the creation of optimized signal communication further comprises separating a plurality of signal codes in the... Petition 870250058780, dated 10 / 07 / 2025, page 64 / 256 59 / 88 Plurality of Air Traffic Controllers. For example, and without limitation, a plurality of air traffic controllers may include one or more formal networks, where formal networks transmit data along a chain of authority and / or are limited to task-related communications. As another non-limiting example, the communication network may include informal networks, in which informal networks transmit data in any direction. In one embodiment, and without limitation, a plurality of air traffic controllers may include a chained path, wherein a chained path, as used herein, is a linear communication path comprising a hierarchy through which data may flow. In one embodiment, and without limitation, a plurality of air traffic controllers may include an all-channel path, wherein an all-channel path, as used herein, is a communication path that is not restricted to a specific direction.For example, and without limitation, data can be transmitted upwards, downwards, laterally, and similarly. In one embodiment, and without limitation, the plurality of flight controllers may include one or more neural networks that assign a weighted value to a transmitted datum. For example, and without limitation, a weighted value may be assigned depending on one or more signals that denote that a flight component is defective and / or in a failed state.

[078] Referring again to Figure 3, the plurality of flight controllers may include a master bus controller. As used in this disclosure, a master bus controller is one or more devices and / or components connected to a bus to initiate a direct memory access transaction, where a bus is one or more terminals in a bus architecture. The master bus controller may communicate using synchronous and / or asynchronous bus control protocols. In one embodiment, the master bus controller may include flight controller 128. In another embodiment, the master bus controller may include one or more receiver-transmitters. Petition 870250058780, dated 10 / 07 / 2025, page 65 / 256 60 / 88 Universal Asynchronous Transport Network Interfaces (UARTs). For example, and without limitation, the master bus controller may include one or more bus architectures that allow a bus to initiate a direct memory access transaction from one or more buses in the bus architectures. As another non-limiting example, the master bus controller may include one or more peripheral devices and / or components to communicate with another peripheral device and / or component and / or the master bus controller. In one embodiment, the master bus controller may be configured to perform bus arbitration. As used in this disclosure, bus arbitration is a method and / or scheme to prevent multiple buses from attempting to communicate with and / or connect to the master bus controller.For example, and without limitation, bus arbitration may include one or more schemes, such as a small computer interface system, wherein a small computer interface system is a set of standards for physical connection and data transfer between peripheral devices and the master bus controller, defining commands, protocols, electrical, optical and / or logical interfaces. In one embodiment, the master bus controller may receive intermediate representation 312 and / or output language from the logical component 320, wherein the output language may include one or more analog-to-digital conversions, low bit rate transmissions, message encryptions, digital signals, binary signals, logical signals, analog signals and the like described above in detail.

[079] Referring again to Figure 3, the master bus controller can communicate with a slave bus. As used in this disclosure, a slave bus is one or more peripheral devices and / or components that initiate a bus transfer. For example, and without limitation, the slave bus may receive one or more asymmetric controls and / or communications from the master bus controller, wherein the slave bus transfers stored data to the controller. Petition 870250058780, dated 10 / 07 / 2025, page 66 / 256 61 / 88 Master bus. In one embodiment, and without limitation, the slave bus may include one or more internal buses, such as, but not limited to, an internal data bus, memory bus, system bus, front-end bus, and the like. In another embodiment, and without limitation, the slave bus may include one or more external buses, such as external flight controllers, external computers, remote devices, printers, aircraft computer systems, flight control systems, and the like.

[080] In one embodiment, and still referring to Figure 3, the control algorithm can optimize signal communication based on the determination of one or more discrete times. For example, and without limitation, the master bus controller can synchronize the timing of the segmented control algorithm by injecting high-priority timing signals into a control bus of the master bus. As used in this disclosure, a high-priority timing signal is information that denotes that the information is important. For example, and without limitation, the high-priority timing signal may denote that a section of the control algorithm is of high priority and must be analyzed and / or transmitted before any other section is analyzed and / or transmitted. In one embodiment, the high-priority timing signal may include one or more priority packets.As used in this disclosure, a priority packet is a formatted unit of data that is communicated between multiple air traffic controllers. For example, and without limitation, the priority packet may denote that a section of the control algorithm should be used and / or is of higher priority than other sections.

[081] Still referring to Figure 3, flight controller 128 can also be implemented using a shared-nothing architecture in which data is cached on the worker; in one mode, this can allow for scalability of the aircraft and / or computing device. Flight controller 128 can include a distributing flight controller. As Petition 870250058780, dated 10 / 07 / 2025, page 67 / 256 62 / 88 used in this disclosure, a distributed flight controller is a component that adjusts and / or controls a plurality of flight components on behalf of a plurality of flight controllers. For example, the distributed flight controller may include a flight controller that communicates with a plurality of additional flight controllers and / or groups of flight controllers. In one embodiment, distributed flight control may include one or more neural networks. For example, a neural network, also known as an artificial neural network, is a network of nodes or data structures with one or more inputs, one or more outputs, and a function that determines outputs based on inputs. These nodes may be arranged in a network, such as, without limitation, a convolutional neural network, which includes an input layer of nodes, one or more intermediate layers, and an output layer of nodes.Connections between nodes can be created through the network training process, in which elements from a training dataset are applied to the input nodes. A suitable training algorithm (such as Levenberg-Marquardt, conjugate gradient, simulated annealing, or other algorithms) is then used to adjust the connections and weights between nodes in adjacent layers of the neural network to produce the desired values ​​in the output nodes. This process is sometimes called deep learning.

[082] Still referring to Figure 3, a node can include, without limitation, a plurality of inputs Xi that can receive numerical values ​​from inputs to a neural network containing the node and / or from other nodes. The node can perform a weighted sum of inputs using weights Wi that are multiplied by the respective inputs Xi. In addition, or alternatively, a bias b can be added to the weighted sum of inputs, so that a shift is added to each unit in the neural network layer that is independent of the input to the layer. The weighted sum can then be inserted into a function (f), which can generate one or more outputs. The weight Wi applied to an input Az can indicate whether the input is excitatory, which indicates that it has a strong influence on one or more outputs y, for example, by Petition 870250058780, dated 10 / 07 / 2025, p. 68 / 256 63 / 88 corresponding weights have a large numerical value and / or an inhibitory effect, indicating that they have a weak influence on the input y, for example, by the corresponding weight having a small numerical value. The values ​​of the Wi weights can be determined by training a neural network using training data, which can be done using any suitable process as described above. In one embodiment, and without limitation, a neural network can receive semantic units as inputs and output vectors that represent such semantic units according to Wi weights that are derived using machine learning processes as described in this disclosure.

[083] Referring again to Figure 3, the flight controller may include a subcontroller 340. As used in this disclosure, a subcontroller is a controller and / or component that is part of a distributed controller as described above; for example, flight controller 128 may be and / or include a distributed flight controller composed of one or more subcontrollers. For example, and without limitation, subcontroller 340 may include any controllers and / or components thereof that are similar to the distributed flight controller and / or flight controller as described above. Subcontroller 340 may include any component of any flight controller as described above. Subcontroller 340 may be implemented in any manner suitable for the implementation of a flight controller as described above.As a further, non-limiting example, the 340 subcontroller may include one or more processors, logic components, and / or computing devices capable of receiving, processing, and / or transmitting data through the distributed flight controller as described above. As another, non-limiting example, the 340 subcontroller may include a controller that receives a signal from a first flight controller and / or first distributed flight controller component and transmits the signal to a plurality of additional subcontrollers and / or flight components. Petition 870250058780, dated 10 / 07 / 2025, p. 69 / 256 64 / 88

[084] Referring again to Figure 3, the flight controller may include a cocontroller 344. As used in this disclosure, a cocontroller is a controller and / or component that joins the flight controller 128 as components and / or nodes of a distributing flight controller, as described above. For example, and without limitation, the cocontroller 344 may include one or more controllers and / or components similar to the flight controller 128. As a further non-limiting example, the cocontroller 344 may include any controller and / or component that connects the flight controller 128 to the distributing flight controller. As another non-limiting example, the cocontroller 344 may include one or more processors, logic components and / or computing devices capable of receiving, processing and / or transmitting data to and / or from the flight controller 128 to the distributed flight control system.Cocontroller 344 can include any component of any flight controller as described above. Cocontroller 344 can be implemented in any manner suitable for implementing a flight controller as described above.

[085] In one embodiment, and with continuous reference to Figure 3, flight controller 128 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, flight controller 128 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 outputs from previous repetitions as inputs to subsequent repetitions, so as to aggregate inputs and / or outputs from 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.The air traffic controller may execute any step or sequence of steps as described. Petition 870250058780, dated 10 / 07 / 2025, page 70 / 256 65 / 88 in this parallel disclosure, how to simultaneously and / or substantially simultaneously execute a step two or more times using two or more parallel chains, processor cores, or the like; the division of tasks between parallel chains and / or 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 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.

[086] With reference now to Figure 4, an exemplary embodiment of a machine learning module 400 that can perform one or more machine learning processes as described in this disclosure is illustrated. The machine learning module can perform determinations, classification and / or analysis steps, methods, processes or the like, as described in this disclosure, using machine learning processes. A machine learning process, as used in this disclosure, is a process that automatically uses training data 404 to generate an algorithm that will be executed by a computing device / module to produce outputs 408 from data provided as inputs 412; this contrasts with a non-machine learning software program, where the commands to be executed are predetermined by a user and written in a programming language.

[087] Referring again to Figure 4, the term training data, as used in this document, refers to data containing correlations that a machine learning process can use to model relationships between two or more categories of data elements. For example, and without limitation, 404 training data may include a plurality of data inputs, each input representing a set of data elements that were recorded, received, and / or generated together; the elements of Petition 870250058780, dated 10 / 07 / 2025, page 71 / 256 66 / 88 data can be correlated by shared existence in a given data entry, by proximity in a given data entry, or similar. Multiple data entries in 404 training data may reveal one or more trends in the correlations between categories of data elements; for example, and without limitation, a higher value of a first data element belonging to a first category of data elements may tend to correlate with a higher value of a second data element belonging to a second category of data elements, indicating a possible proportional relationship or other mathematical relationship linking values ​​belonging to the two categories.Multiple categories of data elements can be related in 404 training data according to various correlations; correlations can indicate causative and / or predictive links between categories of data elements, which can be modeled as relationships, such as mathematical relationships, by machine learning processes as described in more detail below. 404 training data can be formatted and / or organized by categories of data elements, for example, by associating data elements with one or more descriptors corresponding to categories of data elements. As a non-limiting example, 404 training data can include data entered into standardized forms by people or processes, so that the entry of a given data element into a given field on a form can be mapped to one or more category descriptors.The elements in the 404 training data can be linked to category descriptors by tags, tokens, or other data elements; for example, and without limitation, the 404 training data can be provided in fixed-length formats, formats that link data positions to categories such as comma-separated values ​​(CSV) formats, and / or self-descriptive formats such as Extensible Markup Language (XML), JavaScript Object Notation (JSON), or similar, which allows processing or... Petition 870250058780, dated 10 / 07 / 2025, p. 72 / 256 67 / 88 devices detect data categories.

[088] Alternatively or additionally, and continuing to refer to Figure 4, the 404 training data may include one or more elements that are not categorized; that is, the 404 training data may not be formatted or may contain descriptors for some data elements. Machine learning algorithms and / or other processes may classify the 404 training data according to one or more categorizations using, for example, natural language processing algorithms, tokenization, detection of correlated values ​​in raw data and the like; categories may be generated using correlation algorithms and / or other processing algorithms.As a non-limiting example, in a text corpus, phrases comprising n compound words, such as nouns modified by other nouns, can be identified according to a statistically significant prevalence of n-grams containing such words in a particular order; this n-gram can be categorized as a language element, such as a word to be tracked similarly to isolated words, generating a new category as a result of statistical analysis. Similarly, in a data entry that includes some textual data, a person's name can be identified by reference to a list, dictionary, or other compendium of terms, allowing for ad-hoc categorization by machine learning algorithms and / or automated data association in the data entry with descriptors or in a given format.The ability to automatically categorize data inputs can allow the same 404 training data to be applicable to two or more distinct machine learning algorithms, as described in more detail below. The 404 training data used by the 400 machine learning module can correlate any input data, as described in this disclosure, to any output data, as described in this disclosure. As a non-limiting illustrative example, flight elements and / or pilot signals can be inputs, for example. Petition 870250058780, dated 10 / 07 / 2025, page 73 / 256 68 / 88 that an output can be a standalone function.

[089] Referring again to Figure 4, the training data may be filtered, classified and / or selected using one or more supervised and / or unsupervised machine learning processes and / or models, as described in more detail below; such models may include, without limitation, a training data classifier 416. The training data classifier 416 may include a classifier, which, as used in this disclosure, is a machine learning model, as defined below, as a mathematical model, neural network or program generated by a machine learning algorithm known as a classification algorithm, as described in more detail below, which classifies the inputs into categories or data bins, outputs the categories or data bins and / or labels associated with them.A classifier can be configured to generate at least one datum that labels or identifies a set of grouped data that are close by a distance metric, as described below, or something similar. The 400 machine learning module can generate a classifier using a classification algorithm, defined as a process by which a computing device and / or any module and / or component operating on it derives a classifier from 404 training data.Classification can be performed using, but not limited to, linear classifiers such as logistic regression and / or naive Bayes classifiers, nearest neighbor classifiers such as k-nearest neighbor classifiers, support vector machines, least squares support vector machines, Fisher linear discriminant, quadratic classifiers, decision trees, augmented trees, random forest classifiers, quantization of learning vectors, and / or neural network-based classifiers. As a non-limiting example, the 416 training data classifier can classify training data elements into subcategories of flight elements such as torques, forces, thrusts, directions, and... Petition 870250058780, dated 10 / 07 / 2025, page 74 / 256 69 / 88 similar.

[090] Still referring to Figure 4, the machine learning module 400 may be configured to execute a lazy learning process 420 and / or protocol, which may alternatively be called a lazy loading process and / or protocol or call-on-demand, may be a process by which machine learning is conducted after receiving an input to be converted into an output, combining the input and the training set to derive the algorithm to be used to produce the output on demand. For example, an initial set of simulations may be performed to cover an initial heuristic and / or first assumption on an output and / or relationship. As a non-limiting example, an initial heuristic may include a classification of associations between inputs and training data elements 404. The heuristic may include selecting some number of higher-ranking associations and / or training data elements 404.Slow learning can implement any suitable slow learning algorithm, including, without limitation, a K-nearest neighbors algorithm, a lazy and naive Bayes algorithm, or similar; those skilled in the art, upon reviewing the entirety of this disclosure, will be aware of various slow learning algorithms that can be applied to generate results as described in this disclosure, including, without limitation, slow learning applications of machine learning algorithms as described in more detail below.

[091] Alternatively or additionally, and with continuous reference to Figure 4, machine learning processes as described in this disclosure can be used to generate machine learning models 424. A machine learning model, as used in this disclosure, is a mathematical and / or algorithmic representation of a relationship between inputs and outputs, as generated using any machine learning process, including, without limitation, any process as described above, and stored in memory; an input is sent to a model of Petition 870250058780, dated 10 / 07 / 2025, page 75 / 256 70 / 88 machine learning 424 once created, which generates an output based on the relationship that was derived. For example, and without limitation, a linear regression model, generated using a linear regression algorithm, can calculate a linear combination of input data that uses coefficients derived during machine learning processes to calculate an output datum. As another non-limiting example, a 424 machine learning model can be generated by creating an artificial neural network, such as a convolutional neural network comprising an input layer of nodes, one or more intermediate layers, and an output layer of nodes.Connections between nodes can be created through the network training process, in which elements from a 404 training dataset are applied to the input nodes. A suitable training algorithm (such as Levenberg-Marquardt, conjugate gradient, simulated annealing, or other algorithms) is then used to adjust the connections and weights between nodes in adjacent layers of the neural network to produce the desired values ​​in the output nodes. This process is sometimes called deep learning.

[092] Referring again to Figure 4, machine learning algorithms may include at least one supervised machine learning process 428. At least one supervised machine learning process 428, as defined herein, includes algorithms that receive a training set relating a number of inputs to a number of outputs, and seek to find one or more mathematical relationships relating inputs to outputs, wherein each of the one or more mathematical relationships is optimal according to some criterion specified for the algorithm using some scoring function.For example, a supervised learning algorithm might include flight elements and / or pilot signals, as described above, as inputs, autonomous functions as outputs, and a scoring function that represents a desired form of relationship to be detected between inputs and outputs; the scoring function might, for example, seek to maximize the probability that a given... Petition 870250058780, dated 10 / 07 / 2025, page 76 / 256 71 / 88 input and / or combination of elements is associated with a given output to minimize the probability that a given input is not associated with a given output. The scoring function can be expressed as a risk function representing an expected loss of an algorithm that relates inputs to outputs, where the loss is calculated as an error function representing the degree to which a prediction generated by the relationship is incorrect when compared to a given input-output pair provided in the training data 404. Those skilled in the art, upon full review of this disclosure, will be aware of several possible variations of at least one supervised machine learning process 428 that can be used to determine the relationship between inputs and outputs. Supervised machine learning processes may include classification algorithms, as defined above.

[093] Referring again to Figure 4, machine learning processes can include at least unsupervised machine learning processes 432. An unsupervised machine learning process, as used in this document, is a process that derives inferences from datasets without regard to labels; as a result, an unsupervised machine learning process can be free to discover any structure, relationship, and / or correlation provided in the data. Unsupervised processes may not require a response variable; unsupervised processes can be used to find interesting patterns and / or inferences between variables, to determine a degree of correlation between two or more variables, or similar.

[094] Referring again to Figure 4, the machine learning module 400 can be designed and configured to create a machine learning model 424 using techniques for developing linear regression models. Linear regression models can include ordinary least squares regression, which aims to minimize the square of the difference between predicted and actual results according to a standard. Petition 870250058780, dated 10 / 07 / 2025, page 77 / 256 72 / 88 appropriate for measuring this difference (e.g., a vector-space distance norm); the coefficients of the resulting linear equation can be modified to improve minimization. Linear regression models may include ridge regression methods, where the function to be minimized includes the least squares function plus the term multiplying the square of each coefficient by a scalar quantity to penalize large coefficients. Linear regression models may include least absolute selection and shrinkage operator (LASSO) models, in which ridge regression is combined with multiplying the least squares term by a factor of I divided by twice the number of samples. Linear regression models may include a multi-task loop model where the norm applied to the least squares term of the loop model is the Frobenius norm, which is equivalent to the square root of the sum of the squares of all terms.Linear regression models may include the elastic network model, a multitasking elastic network model, a minimum angle regression model, a LARS loop model, an orthogonal matching chase model, a Bayesian regression model, a logistic regression model, a stochastic gradient descent model, a perceptron model, a passive-aggressive algorithm, a robustness regression model, a Huber regression model, or any other suitable model that may occur to persons skilled in the art upon reviewing the entirety of this disclosure.Linear regression models can be generalized in a way to polynomial regression models, where a polynomial equation (e.g., a quadratic, cubic, or higher-order equation) that provides the best fit between predicted output / actual output is sought; methods similar to those described above can be applied to minimize error functions, as will be apparent to those skilled in the art upon reviewing the entirety of this disclosure.

[095] Continuing to refer to Figure 4, machine learning algorithms may include, without limitation, linear discriminant analysis. The algorithm Petition 870250058780, dated 10 / 07 / 2025, page 78 / 256 Machine learning algorithms may include quadratic discriminant analysis. Machine learning algorithms may include kernel crest regression. Machine learning algorithms may include support vector machines, which include, without limitation, regression processes based on support vector classification. Machine learning algorithms may include stochastic gradient descent algorithms, which include classification and regression algorithms based on stochastic gradient descent. Machine learning algorithms may include nearest neighbor algorithms. Machine learning algorithms may include Gaussian processes, such as Gaussian process regression. Machine learning algorithms may include cross-decomposition algorithms, which include partial least squares and / or canonical correlation analysis.Machine learning algorithms can include naive Bayes methods. Machine learning algorithms can include decision tree-based algorithms, such as decision tree classification or regression algorithms. Machine learning algorithms can include ensemble methods, such as bagging metaestimator, random tree forest, AdaBoost, gradient tree boosting, and / or voting classification methods. Machine learning algorithms can include neural network algorithms, which includes convolutional neural network processes.

[096] With reference now to Figure 5, it is a flow diagram of an exemplary method 500 for flight control of an electric aircraft. In step 505, method 500 includes the detection, by a sensor, of pilot input from a pilot control, wherein the pilot input is transmitted to a flight controller of an electric aircraft, wherein the electric aircraft includes a plurality of flight components coupled to an electric aircraft, wherein the plurality of flight components may include a plurality of redundant control surfaces; and a plurality of redundant low-voltage buses communicatively connected to the plurality of flight components, wherein Petition 870250058780, dated 10 / 07 / 2025, page 79 / 256 74 / 88 A failure in one redundant low-voltage busbar of the plurality of redundant low-voltage busbars does not affect the operability of the electric aircraft. Step 505 can be implemented as described in Figures 1-4. One redundant control surface of the plurality of redundant control surfaces may include at least two ailerons located on one wing of the electric aircraft. One redundant control surface of the plurality of redundant control surfaces may include at least two elevators located on one side of the electric aircraft. The pilot control may be configured to control the pitch, roll, and yaw of the electric aircraft. The pilot input may additionally include an attitude command that describes a transition from vertical to horizontal flight of the electric aircraft.In step 510, method 500 includes the generation of a fault datum corresponding to a deactivation of one flight component from the plurality of flight components, for example and as implemented in Figures 1-4. The pilot control can be configured to receive the fault datum from the sensor and subsequently generate an attitude command for a second flight component from the plurality of components.

[097] It should be noted that any one or more of the aspects and embodiments described herein may be conveniently implemented using one or more machines (e.g., one or more computing devices 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 descriptive report, as will be apparent to those of ordinary skill in computing techniques. Appropriate software coding may be readily prepared by skilled programmers based on the teachings of this disclosure, as will be apparent to those of ordinary skill in software techniques. The aspects and embodiments discussed above employing software and / or software modules may also include appropriate hardware to assist in the implementation of the Petition 870250058780, dated 10 / 07 / 2025, page 80 / 256 75 / 88 executable instructions of the software machine and / or software module.

[098] 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 ROM memory device, a random-access RAM memory device, 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. 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 can be included as a data transport signal embedded in a data carrier where the signal encodes a sequence of instructions, or a portion 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.

[099] Examples of a computing device include, but without Petition 870250058780, dated 10 / 07 / 2025, page 81 / 256 76 / 88 limitation, an electronic book reader, a computer workstation, a terminal computer, a server computer, a portable device (e.g., a tablet computer, a smartphone, etc.), a web tool, 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.

[100] Figure 6 shows a diagrammatic representation of an embodiment of a computing device in the exemplary form of a computer system 600 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 600 includes a processor 604 and a memory 608 that communicate with each other and with other components by means of a bus 612.The 612 bus can include any of several types of bus structures, including, but 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.

[101] The 604 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 logic unit (ALU), which may be regulated with a state machine and driven by operational memory and / or sensor inputs; the 604 processor may be organized according to the Von Neumann and / or Harvard architecture as an example. Petition 870250058780, dated 10 / 07 / 2025, page 82 / 256 77 / 88 not limiting. The 604 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).

[102] Memory 608 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 616 (BIOS), including basic routines that help transfer information between elements within the computer system 600, such as during initialization, may be stored in memory 608. Memory 608 may also include (e.g., stored on one or more machine-readable media) instructions (e.g., software) 620 that incorporate any one or more of the aspects and / or methodologies of the present disclosure. In another example, memory 608 may include any number of program modules, including, but not limited to, an operating system, one or more application programs, other program modules, program data, and any combination thereof.

[103] The 600 computer system may also include a 624 storage device. Examples of a storage device (e.g., storage device 624) 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 624 storage device may be connected to the 612 bus by an appropriate interface (not shown). Examples of interfaces include, but are not limited to, SCSI, Advanced Technology Interface (ATA), Serial ATA, bus Petition 870250058780, dated 10 / 07 / 2025, page 83 / 256 78 / 88 Universal Serial (USB), IEEE 1394 (FIREWIRE), and any combination thereof. In one example, the storage device 624 (or one or more of its components) may be removablely connected to the computer system 600 (e.g., via an external port connector (not shown)). In particular, the storage device 624 and an associated machine-readable medium 628 may provide non-volatile and / or volatile storage of machine-readable instructions, data structures, program modules, and / or other data for the computer system 600. In one example, the software 620 may reside, wholly or partially, on a machine-readable medium 628. In another example, the software 620 may reside, wholly or partially, on the processor 604.

[104] The computer system 600 may also include an input device 632. In one example, a user of the computer system 600 may enter commands and / or other information into the computer system 600 by means of the input device 632. Examples of an input device 632 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 cursor control device (e.g., a mouse), a touchpad, an optical scanner, a video capture device (e.g., a still camera, a video camera), a touch screen, and any combinations thereof.Input device 632 can be connected to bus 612 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 bus 612, and any combination thereof. Input device 632 may include a touchscreen interface which may be part of or separate from screen 636, discussed later. Input device 632 may be used as a user selection device for... Petition 870250058780, dated 10 / 07 / 2025, page 84 / 256 79 / 88 select one or more graphical representations in a graphical interface, as described above.

[105] A user may also enter commands and / or other information into the computer system 600 via storage device 624 (e.g., a removable disk drive, a flash drive, etc.) and / or network interface device 640. A network interface device, such as network interface device 640, may be used to connect the computer system 600 to one or more of a variety of networks, such as network 644, and one or more remote devices 648 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, a building, a campus, or other relatively small geographical 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. A network, such as network 644, may employ a wired and / or wireless communication mode. In general, any network topology may be used. Information (e.g., data, software 620, etc.) may be communicated to and / or from computer system 600 via network interface device 640.

[106] The computer system 600 may additionally include a video adapter 652 for communicating a displayable image to a display device, such as the display device 636. 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 652 and the display device 636 may be used in combination with the Petition 870250058780, dated 10 / 07 / 2025, page 85 / 256 80 / 88 processor 604 to provide graphical representations of aspects of the present disclosure. In addition to a display device, the computer system 600 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 612 by means of a peripheral interface 656. 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.

[107] 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 herein is merely illustrative of the application of the principles of the present invention. In addition, although specific methods herein may be illustrated and / or described as being performed in a specific order, the ordering is highly variable within the common ability to achieve methods, systems, and software according to the present disclosure.Consequently, this description should be taken only as an example, and not to limit the scope of this invention.

[108] 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. EXAMPLE CLAUSES Petition 870250058780, dated 10 / 07 / 2025, p. 86 / 256 81 / 88

[109] In some cases, one or more components may be referred to in this document as configured for, configurable for, operable / operable for, adapted / adaptable, capable of, conformable / compliant with, etc. Those skilled in the art will recognize that such terms (e.g., configured for) may generally encompass active-state components and / or inactive-state components and / or standby-state components, unless the context requires otherwise.

[110] As used in this document, the term based on can be used as a synonym for based, at least in part, on and based at least partially on.

[111] As used in this document, the terms comprise / that comprises / comprising and includes / that includes / included and their equivalents may be used interchangeably. An apparatus, system or method comprising A, B and C includes A, B and C, but may also include other components (e.g., D). That is, the apparatus, system or method is not limited to components A, B and C.

[112] Although the object has been described in language specific to structural features and / or methodological acts, it should be understood that the object defined in the appended claims is not necessarily limited to the specific features or acts described.

[113] A: A flight control system for an aircraft, wherein the flight control system comprises: a plurality of flight components coupled to an aircraft, wherein the plurality of flight components comprises a plurality of redundant control surfaces; and a plurality of redundant low-voltage buses communicatively connected to the plurality of flight components, wherein a failure in one redundant low-voltage bus of the plurality of redundant low-voltage buses does not affect the operability of the aircraft.

[114] B: The flight control system of paragraph A, comprising Petition 870250058780, dated 10 / 07 / 2025, page 87 / 256 82 / 88 additionally a flight controller communicatively connected to the plurality of redundant control surfaces and configured to control the plurality of redundant control surfaces.

[115] C: The flight control system of paragraph A or B, which additionally comprises a pilot control communicatively connected to the air traffic controller, wherein the pilot control is configured to transmit at least one pilot input to the air traffic controller.

[116] D: The flight control system of paragraph C, which further comprises a sensor communicatively connected to the pilot control, wherein the sensor is configured to detect an input from the pilot control and transmit the pilot input to the flight controller.

[117] E: The flight control system of any of the AD paragraphs, wherein a redundant control surface of the plurality of redundant control surfaces comprises at least two ailerons located on a fixed wing of the aircraft.

[118] F: The flight control system of any of the paragraphs AE, wherein a redundant control surface of the plurality of redundant control surfaces comprises at least two elevators located on one side of the aircraft.

[119] G: The flight control system of any of the AF paragraphs, in which the plurality of flight components and the plurality of redundant low-voltage buses are categorized into a plurality of control sets.

[120] H: The flight control system of paragraph G, in which a set of control of the plurality of control sets is located on each wing of the aircraft.

[121] I: The flight control system of paragraph D, in which a command set of the plurality of command sets comprises at least two groups of components.

[122] J: The flight control system of paragraph I, in which a group of Petition 870250058780, dated 10 / 07 / 2025, page 88 / 256 83 / 88 components of at least two component groups comprise a group of components used in the flight control of an aircraft part from a plurality of redundant components in a control assembly.

[123] K: The flight control system of paragraph C, in which the pilot's control is configured to control pitch, roll and yaw of the aircraft.

[124] L: The flight control system of any of the AK paragraphs, wherein a pilot input additionally comprises an attitude command describing a transition from vertical to horizontal flight of the aircraft.

[125] M: The flight control system of paragraph D, in which the sensor is additionally configured to: detect an attitude command from a pilot control; determine that a flight component of the plurality of flight components is deactivated; and generate a fault datum corresponding to the deactivation of the flight component.

[126] N: The flight control system of paragraph M, in which the pilot control is configured to receive the sensor fault datum and subsequently generate an attitude command for a second flight component from the plurality of flight components.

[127] O: A method for controlling the flight of an aircraft, wherein the method comprises: detecting, by a sensor, the pilot input of a pilot control, wherein the pilot input is transmitted to an aircraft flight controller, wherein the aircraft comprises: a plurality of flight components coupled to an aircraft, wherein the plurality of flight components comprises a plurality of redundant control surfaces; and a plurality of redundant low-voltage buses communicatively connected to the plurality of flight components, wherein a failure in a redundant low-voltage bus of the plurality of redundant low-voltage buses does not affect the operability of the aircraft; and generating a fault datum corresponding to a deactivation of a flight component of the plurality of flight components. Petition 870250058780, dated 10 / 07 / 2025, page 89 / 256 84 / 88

[128] P: The method of paragraph O, in which a redundant control surface of the plurality of redundant control surfaces comprises at least two ailerons located on a fixed wing of the aircraft.

[129] Q: The O or P paragraph method, wherein a redundant control surface of the plurality of redundant control surfaces comprises at least two elevators located on one side of the aircraft.

[130] R: The method of any of the OQ paragraphs, in which the pilot's control is configured to control the pitch, roll and yaw of the aircraft.

[131] S: The method of either of the OR paragraphs, in which the pilot input additionally comprises an attitude command describing a transition from vertical to horizontal flight of the aircraft.

[132] T: The method of any of the OS paragraphs, in which the generation of the fault datum comprises receiving, by the pilot control, the fault datum from the sensor and subsequently generating an attitude command for a second flight component from the plurality of components.

[133] U: A flight control system comprising: a first flight component coupled to an aircraft, wherein the first flight component has a first control surface actuated by a first actuator that adjusts a flight characteristic of the aircraft when actuated; a second flight component coupled to the aircraft, wherein the second flight component has a second control surface actuated by a second actuator that adjusts the flight characteristic of the aircraft when actuated, wherein the second control surface is redundant with respect to the first control surface; a sensor system configured to detect a failure in the actuation of the first flight component or the second flight component and to emit a failure datum; and a flight controller configured to: receive an input that directs control of the aircraft; provide an output to the first actuator and the second actuator in response to the input; receive the failure datum;and provide an alert in response to the failure date. Petition 870250058780, dated 10 / 07 / 2025, page 90 / 256 85 / 88

[134] V: The U-point flight control system, wherein: the first flight component comprises a first aileron; the second flight component comprises a second aileron; and the first aileron is adjacent to the second aileron on a first wing of the aircraft.

[135] W: The flight control system of paragraphs U or V, wherein the second control surface which is redundant with respect to the first control surface comprises the second control surface positioned adjacent and configured to control the flight characteristic independently in the event of failure of the first control surface.

[136] X: The flight control system of any of the UW paragraphs, which additionally comprises a low voltage bus providing a first communication channel from the flight controller to the first actuator and a second communication channel from the flight controller to the second actuator, the second communication channel being redundant to the first communication channel.

[137] Y: The flight control system of any of the UX paragraphs, in which the sensor system is further configured to: detect the flight controller output; determine a response from the first flight component that indicates a responsiveness or a non-responsiveness; and generate the fault datum when the response is indicative of non-responsiveness.

[138] Z: The flight control system of any of the UZ paragraphs, in which, in response to the fault datum, the flight controller provides a second output to at least one of the first flight components or the second flight component.

[139] AA: The flight control system of paragraph Z, wherein the control provided to the second flight component comprises a second magnitude of actuation which differs from a first magnitude of actuation of the output in response to control only from the second control surface.

[140] AB: A method comprising: receiving, in an air traffic controller of Petition 870250058780, dated 10 / 07 / 2025, page 91 / 256 86 / 88 an aircraft; an input describing a command for controlling an aircraft; to determine, by the flight controller and in response to the input, a first output for controlling an aircraft flight control system, wherein the flight control system comprises a first control surface actuated by a first actuator and a second control surface actuated by a second actuator; to transmit the first output to the first actuator; to transmit the first output to the second actuator; to receive, at the flight controller, sensor data from a sensor system configured to detect a fault in the actuation of the first actuator or the second actuator; and to determine, by the flight controller and based at least in part on the sensor data, a fault in the actuation of the first control surface or the second control surface.

[141] AC: The AB paragraph method, in which determining the actuation failure involves determining a failure in communication between the air traffic controller and the first actuator.

[142] AD: The AB or AC paragraph method, in which the first control surface and the second control surface are positioned on an aircraft wing, with the first control surface adjacent to the second control surface along a length of the wing.

[143] AE: The method of any of the paragraphs AB-AD, wherein: the sensor data comprise a sensor measuring the movement of the first control surface and the second control surface; and determining the fault comprised determining, based on the sensor data, the lack of movement of the first control surface.

[144] AF: The method of any of the AB-AE paragraphs, wherein the first control surface is positioned adjacent to the second control surface on an aircraft structure, and wherein the first control surface and the second control surface comprise at least one of the following: ailerons; elevators; flaps; rudders; stabilizers; or airfoils.

[145] AG: The method of any of the AB-AF paragraphs, which also includes the Petition 870250058780, dated 10 / 07 / 2025, p. 92 / 256 87 / 88 generation, by the flight controller and in response to the fault, of a second output to the first actuator or to the second actuator associated with the output.

[146] AH: The AG paragraph method, in which the first output is configured to cause movement in the first actuator and in the second actuator of first magnitude and in response to the determination of a failure in the actuation of the first control surface, the second output is configured to cause movement in the second actuator of second magnitude, the second magnitude being greater than the first magnitude.

[147] A1: An aircraft comprising: a fuselage; a wing; a first flight component coupled to the wing, wherein the first flight component has a first control surface actuated by a first actuator; a second flight component coupled to the wing, wherein the second flight component has a second control surface actuated by a second actuator, wherein the second control surface is redundant with respect to the first control surface; a sensor system configured to detect a fault in the actuation of the first flight component or the second flight component and to issue a fault datum; and a flight controller configured to: receive an input that directs control of the aircraft; provide an output to the first flight component and the second flight component in response to the input; and determine a fault in at least one of the components of the first flight component or the second flight component in response to the fault datum.

[148] AJ: The aircraft of paragraph Al, wherein: the first flight component comprises a first aileron; the second flight component comprises a second aileron; and the first aileron is adjacent to the second aileron on a first wing of the aircraft.

[149] AK: The aircraft of paragraph Al or AJ, additionally comprising a low-voltage busbar providing a first communication channel from the flight controller to the first actuator and a second communication channel from the flight controller to the second actuator, the second Petition 870250058780, dated 10 / 07 / 2025, page 93 / 256 88 / 88 redundant communication channel for the first communication channel.

[150] AL: The aircraft of any of the AI-AK paragraphs, in which the sensor system is further configured to: detect the flight controller output; determine a response from the first flight component or the second flight component that indicates a responsiveness or a non-responsiveness; and generate the fault datum when the response is indicative of non-responsiveness.

[151] AM: The aircraft of any of the AI-AL paragraphs, in which the second control surface that is redundant with respect to the first control surface comprises the second control surface positioned adjacent and configured to control a flight characteristic independently in the event of failure of the first control surface.

[152] AN: Aircraft of any of the paragraphs Al-AM, in which flight controller output is provided for the first flight component and the second flight component; and in response to the flight controller determining a fault in the first flight component, the flight controller is configured to provide a second output for the second flight component. Petition 870250058780, dated 10 / 07 / 2025, page 94 / 256

Claims

1 / 4 CLAIMS 1. FLIGHT CONTROL SYSTEM FOR AN AIRCRAFT, wherein the flight control system is characterized by comprising: a plurality of flight components coupled to an aircraft, wherein the plurality of flight components comprises a plurality of redundant control surfaces; and a plurality of redundant low-voltage buses communicatively connected to the plurality of flight components, wherein a failure in one redundant low-voltage bus of the plurality of redundant low-voltage buses does not affect the operability of the aircraft.

2. FLIGHT CONTROL SYSTEM, according to claim 1, characterized by further comprising a flight controller communicatively linked to a plurality of redundant control surfaces and configured to control the plurality of redundant control surfaces.

3. FLIGHT CONTROL SYSTEM, according to claim 2, characterized by further comprising a pilot control communicatively connected to the flight controller, wherein the pilot control is configured to transmit at least one pilot input to the flight controller and further comprising a sensor communicatively connected to the pilot control, wherein the sensor is configured to detect a pilot input from the pilot control and transmit the pilot input to the flight controller.

4. FLIGHT CONTROL SYSTEM, according to claim 1, characterized by the plurality of flight components and the plurality of redundant low-voltage busbars being categorized into a plurality of control assemblies, wherein the control assembly of the plurality of control assemblies is located on each wing of the aircraft.

5. FLIGHT CONTROL SYSTEM, according to claim 3, characterized by a control set of a plurality of control sets comprising at least two groups of components. Petition 870260041933, dated 05 / 05 / 2026, page 7 / 23 2 / 4 6. FLIGHT CONTROL SYSTEM, according to claim 5, characterized by a group of components of at least two groups of components comprising a group of components used in the flight control of an aircraft part or a plurality of redundant components in a control assembly.

7. FLIGHT CONTROL SYSTEM, according to claim 3, characterized in that the sensor is additionally configured to: detect an attitude command from a pilot control; determine that a flight component from the plurality of flight components is deactivated; and generate a fault data corresponding to the deactivation of the flight component.

8. FLIGHT CONTROL SYSTEM, according to claim 7, characterized in that the pilot control is configured to receive sensor fault data and subsequently generate an attitude command for a second flight component from the plurality of flight components.

9. A METHOD FOR AIRCRAFT FLIGHT CONTROL, wherein the method is characterized by comprising: detecting, by a sensor, the pilot's input from a pilot control, wherein the pilot's input is transmitted to an aircraft flight controller, wherein the aircraft comprises: a plurality of flight components coupled to an aircraft, wherein the plurality of flight components comprises a plurality of redundant control surfaces; and a plurality of redundant low-voltage buses communicatively connected to the plurality of flight components, wherein a failure in a redundant low-voltage bus of the plurality of redundant low-voltage buses does not affect the operability of the aircraft; and generating a fault data corresponding to a deactivation of a flight component of the plurality of flight components.

10. METHOD, according to claim 9, characterized by generating the fault data Petition 870260041933, dated 05 / 05 / 2026, page 8 / 23 3 / 4, understanding, receiving, through pilot control, the fault data from the sensor and, subsequently, generating an attitude command for a second flight component from the plurality of components.

11. FLIGHT CONTROL SYSTEM characterized by comprising: a first flight component coupled to an aircraft, wherein the first flight component has a first control surface actuated by a first actuator that adjusts a flight characteristic of the aircraft when actuated; a second flight component coupled to the aircraft, wherein the second flight component has a second control surface actuated by a second actuator that adjusts the flight characteristic of the aircraft when actuated, wherein the second control surface is redundant with respect to the first control surface; a sensor system configured to detect a fault in the actuation of the first flight component or the second flight component and to output fault data; and a flight controller configured to: receive an input that directs control of the aircraft; provide an output to the first actuator and the second actuator in response to the input; receive the fault data;and provide an alert in response to the failure data.

12. FLIGHT CONTROL SYSTEM, according to claim 11, characterized by further comprising a low-voltage bus providing a first communication channel from the flight controller to the first actuator and a second communication channel from the flight controller to the second actuator, the second communication channel being redundant to the first communication channel.

13. FLIGHT CONTROL SYSTEM, according to claim 11, characterized in that the sensor system is additionally configured to: Petition 870260041933, dated 05 / 05 / 2026, page 9 / 23 4 / 4 detect the flight controller output; determine a response from the first flight component indicating a responsiveness or a non-responsiveness; and generate fault data when the response is indicative of a non-responsiveness.

14. FLIGHT CONTROL SYSTEM, according to claim 11, characterized in that, in response to fault data, the flight controller provides a second output to at least one of the first flight components or to the second flight component.

15. FLIGHT CONTROL SYSTEM, according to claim 14, characterized in that the control provided to the second flight component comprises a second magnitude of actuation that differs from a first magnitude of actuation of the output in response to control only from the second control surface. Petition 870260041933, dated 05 / 05 / 2026, page 10 / 23

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