Abstract: Disclosed herein is a system and method for effector reboot on an electric aircraft during flight. An effector controller may perform a power on built-in test on boot. An effector controller may selective perform an additional built-in test (ABIT) on boot based on instructions from a flight controller. The flight controller may use flags to indicate the necessity of an ABIT on boot. The effector controller may not perform an ABIT during flight. A backup controller may be used to send standard commands to an effector controller but may not sent an ABIT command.

Abstract: An apparatus and method for calculating anticipated energy consumption for electric aircraft are disclosed. The method may include receiving flight plan data and determining at least a flight phase as a function of the flight plan data. Further, the method may include estimating a duration and energy consumption rate for the at least a flight phase, estimating a usable energy capacity of the electric aircraft, and determining a value of additional energy to add to the electric aircraft.

Abstract: Systems and methods for reducing common mode failures in flight control of an aircraft is disclosed herein. Reducing common mode failures includes using dissimilar components. Dissimilar components found in flight control of an aircraft may include sensors, effectors, command processors, and monitor processors. One or more flight controllers are used to transmit commands to effectors and monitor effectors using dissimilar sensors.

Abstract: A system for flight control in electric aircraft includes a flight controller configured to provide an initial vehicle torque signal including a plurality of attitude commands. The system includes a mixer configured to receive the initial vehicle torque signal and a vehicle torque limit, receive prioritization data including a prioritization datum corresponding to each of the plurality of attitude command, determine a plurality of modified attitude commands as a function of the vehicle torque limit, the attitude commands, and the prioritization data, generate, as a function of modified attitude commands, an output torque command including the initial vehicle torque signal adjusted as a function of the vehicle torque limit, generate, as a function of the output torque command, a remaining vehicle torque. The system includes a display, wherein the display is configured to present, to a user, the remaining vehicle torque and the output torque command.

Abstract: A system for redistributing electrical load in an electric aircraft. The system includes a ring bus and a controller communicatively connected to the ring bus. The ring bus includes a plurality of bus sections including a first bus section and a second bus section. The controller is configured to receive a fault datum indicative of a fault associated with one of a first energy source and a second energy source, actuate, as a function of the fault datum, at least a switch to electrically connect the first bus section and the second bus section so as to form an electrical merger of the first bus section and the second bus section, and redistribute the electrical load to compensate for the fault associated with one of the first energy source and the second energy source. A method of redistributing electrical load in an electric aircraft is also provided.

Abstract: A system for distributed pilot control of an aircraft includes a plurality of flight components, an aircraft control located within the aircraft, and an aircraft component attached to a flight component of the plurality of flight components, wherein the aircraft component is configured to receive, from a command sensor attached to the aircraft control, an aircraft command, obtain, from an attitude sensor, an aircraft orientation, receive, as a function of a notification unit, a pilot signal, and command the flight component to produce a response command as a function of the pilot signal.

Abstract: A system for redistributing electrical load in an electric aircraft. The system includes a ring bus and a controller communicatively connected to the ring bus. The ring bus includes a plurality of bus sections including a first bus section and a second bus section. The controller is configured to receive a fault datum indicative of a fault associated with one of a first energy source and a second energy source, actuate, as a function of the fault datum, at least a switch to electrically connect the first bus section and the second bus section so as to form an electrical merger of the first bus section and the second bus section, and redistribute the electrical load to compensate for the fault associated with one of the first energy source and the second energy source. A method of redistributing electrical load in an electric aircraft is also provided.

Abstract: A system for a distributed pilot control of an aircraft is disclosed. The system includes a plurality of flight components. The system also includes an aircraft control located within the aircraft. The system includes an aircraft component attached to a flight component of the plurality of flight components. The aircraft component is configured to receive, from a command sensor attached to the aircraft control, an aircraft command. The aircraft component is configured to obtain, from an attitude sensor, an aircraft orientation. The aircraft component is configured to receive, as a function of a notification unit, a pilot signal. The aircraft component is additionally configured to command the flight component to produce a response command as a function of the pilot signal.

Abstract: A system and method for an electric aircraft coaching simulator is illustrated. The simulator includes a pilot control that is configured to generate a pilot command. The simulator includes a processor that is configured to receive optimized flight data, simulate a battery performance of an electric aircraft as a function of the received pilot command and generate an optimal flight recommendation based off the optimized flight data. The simulation model is configured to communicatively connect with the flight simulator to mimic a real flight situation. Optimized flight data from other pilots can be used to coach pilots how to fly with more energy efficiency.

Abstract: A system for overvoltage protection on loads for use in an electric aircraft is presented. The system includes an energy storage element configured to produce an electrical output, a bus element, wherein the bus is configured to transfer the electrical output from the energy storage element, a plurality of inverters, wherein each inverter is configured to generate a regulated output as a function of the electrical output and detect an overvoltage output as a function of the regulated output, and a plurality of load devices connected to the plurality of inverters, wherein each load device includes a fault protection device.

Abstract: Aspects relate to methods and systems for reversionary flight control for an electrical vertical take-off and landing (eVTOL) aircraft. An exemplary system includes a pilot control, a sensor configured to sense and transmit analog control data associated with a pilot interaction with the pilot control, a pilot interface module configured to receive the analog control data, convert the analog control data to digital control data, and transmit digital control, an actuator, and a flight controller. The flight controller may be configured to receive the digital control data, determine a primary command datum as a function of the digital control data, transmit the primary command datum to the actuator, determine that the digital control signal is non-functional, receive the analog control data, determine a reversionary command datum as a function of the analog control data, and transmit the reversionary command datum to the actuator.

Abstract: A system for overvoltage protection on loads for use in an electric aircraft is presented. The system includes an energy storage element configured to produce an electrical output, a bus element, wherein the bus is configured to transfer the electrical output from the energy storage element, a plurality of inverters, wherein each inverter is configured to generate a regulated output as a function of the electrical output and detect an overvoltage output as a function of the regulated output, and a plurality of load devices connected to the plurality of inverters, wherein each load device includes a fault protection device.

Abstract: A system of fall back flight control configured for use in electric aircraft includes an input control configured to receive a pilot input and generate a control datum. System includes a flight controller communicatively coupled to the input control and configured to receive the control datum and generate an output datum. The system includes the actuator having a primary mode in which the actuator is configured to move the at least a portion of the electric aircraft as a function of the output datum and a fall back mode in which the actuator is configured to move the at least a portion of the aircraft as a function of the control datum. The actuator configured to receive the control datum, receive the output datum, detect a loss of communication with the flight controller, and select the fall back mode as a function of the detection.

Abstract: The present disclosure is generally directed to a flight control system and method of flight control for an electric aircraft. The system includes a pilot input communicatively connected to an electric aircraft, wherein the pilot input is configured to receive an input datum, and plurality of flight components communicatively connected to the electric aircraft, wherein the plurality of flight components includes a plurality of control surfaces. The system also includes a flight controller, wherein the flight controller is configured to determine a phase of flight, determine a command datum to control a position of the plurality of control surfaces as a function of the input datum, and command, when the phase of flight is determined to be hover, the plurality of control surfaces using the command datum.

Abstract: Some aspects relate to systems and methods for fly-by-wire reversionary flight control including a pilot control, a plurality of sensors configured to: sense control data associated with the pilot control, and transmit the control data, a first actuator communicative with the plurality of sensors configured to receive the control data, determine a first command datum as a function of the control data and a distributed control algorithm, and actuate a first control element according to the first command datum.

Abstract: Provided in this disclosure is a high voltage distribution system of an electric aircraft. The system includes a power source mechanically connected to an electric aircraft, where the power source is configured to supply power to the electric aircraft. The system also includes a flight component mechanically connected to the electric aircraft. The system also includes a distribution component configured to control the providing of power to and from the power source and the flight component as needed during recharging and/or operation of the electric aircraft.

Abstract: A system for redistributing electrical load in an electric aircraft. The system includes a ring bus and a controller communicatively connected to the ring bus. The ring bus includes a plurality of bus sections including a first bus section and a second bus section. The controller is configured to receive a fault datum indicative of a fault associated with one of a first energy source and a second energy source, actuate, as a function of the fault datum, at least a switch to electrically connect the first bus section and the second bus section so as to form an electrical merger of the first bus section and the second bus section, and redistribute the electrical load to compensate for the fault associated with one of the first energy source and the second energy source. A method of redistributing electrical load in an electric aircraft is also provided.

Abstract: A system for flight control in electric aircraft includes a flight controller configured to provide an initial vehicle torque signal including a plurality of attitude commands. The system includes a mixer configured to receive the initial vehicle torque signal and a vehicle torque limit, receive prioritization data including a prioritization datum corresponding to each of the plurality of attitude command, determine a plurality of modified attitude commands as a function of the vehicle torque limit, the attitude commands, and the prioritization data, generate, as a function of modified attitude commands, an output torque command including the initial vehicle torque signal adjusted as a function of the vehicle torque limit, generate, as a function of the output torque command, a remaining vehicle torque. The system includes a display, wherein the display is configured to present, to a user, the remaining vehicle torque and the output torque command.

Abstract: A drive circuit comprising a DC bus configured to supply power to a load, a first fuel cell coupled to the DC bus and configured to provide a first power output to the DC bus, and a second fuel cell coupled to the DC bus and configured to provide a second power output to the DC bus supplemental to the first fuel cell. The drive circuit further includes an energy storage device coupled to the DC bus and configured to receive energy from the DC bus when a combined output of the first and second fuel cells is greater than a power demand from a load, and provide energy to the DC bus when the combined output of the first and second fuel cells is less than the power demand from the load.

Abstract: A system and method for flight control of an aircraft, the flight control system including 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 communicatively connected to the plurality of flight components, wherein a failure in a redundant low voltage bus of the plurality of redundant low voltage busses does not impact the operability of the aircraft.