Abstract: A system for estimating percentage torque produced by a propulsor configured for use in an electric aircraft, the system including a propulsor, the propulsor configured to generate output torque. The system including a sensor, the sensor configured to detect the output torque and generate an output torque datum. The system including a flight controller including a computing device configured to receive an output torque datum, receive an ideal propulsor model, the ideal propulsor model including at least a performance parameter, generate a model torque datum, including a model torque datum threshold, as a function of the at least a performance parameter, generate a percentage datum as a function of the output torque datum and model torque datum, and determine, at least an obstruction datum correlated to the torque percentage datum, and display torque percentage datum and the at least an obstruction datum.

Abstract: A system for landing spot analysis including an electric aircraft and a sensor connected to the electric aircraft. The sensor is configured to detect a landing datum relating to a possible landing spot, wherein the landing datum comprises information regarding the physical properties of the possible landing spot. The system also including a controller onboard the electric aircraft and communicatively connected to the sensor. The controller is configured to receive a command identifying at least the possible landing spot, receive the landing datum from the sensor, generate a landing determination as a function of the landing datum, wherein the landing determination relates to the suitability of the possible landing spot and generating the landing determination includes transmitting a landing request to air traffic control, and transmit the landing determination to a pilot.

Abstract: In an aspect, a propulsor gauge is provide that provides guidance during a transition of a mode of operation of an electric aircraft. Propulsor gauge may include a processor configured to identify a current thrust envelope parameter of one or more propulsors of electric aircraft. Processor may also determine a recommended range as a function of the propulsor parameter, where the recommended range includes a lower threshold and an upper threshold. The recommended range and thrust envelope parameter may then be shown on a display of propulsor gauge, where a measurement of current thrust envelope parameter relative to recommended range may be represented by an indicator.

Abstract: A system for estimating percentage torque produced by a propulsor configured for use in an electric aircraft, the system including a propulsor, the propulsor configured to generate output torque. The system including a sensor, the sensor configured to detect the output torque and generate an output torque datum. The system including a flight controller including a computing device configured to receive an output torque datum, receive an ideal propulsor model, the ideal propulsor model including at least a performance parameter, generate a model torque datum, including a model torque datum threshold, as a function of the at least a performance parameter, generate a percentage datum as a function of the output torque datum and model torque datum, and determine, at least an obstruction datum correlated to the torque percentage datum, and display torque percentage datum and the at least an obstruction datum.

Abstract: Braking systems and methods for an electrical vertical takeoff and landing aircraft are provided. A braking system may contain a pilot control device, brakes, wheels, sensors, and a controller. Pilot controls the pilot control device to transmit information to the controller such that the aircraft will slow down.

Abstract: A system for establishing a primary function display for an electrical vertical takeoff and landing aircraft. The system further includes a plurality of sensors that detects at least a metric and generates at least a datum based on the at least a metric. Specifically, state of charge is at least generated based on the performance metric of an energy source. The system further includes a display to show the at least a datum. The system further includes a controller that receives the at least a datum and generates a visual to the pilot.

Abstract: In an aspect of the present disclosure is a system of automated fleet management for aerial vehicles, including a first aerial vehicle, the aerial vehicle comprising: a first sensor configured to measure an external metric and generate external datum based on the external metric; and a second sensor configured to measure an aircraft metric and generate aircraft datum based on the aircraft metric; and a computing device operating on the first aerial vehicle, the computing device communicatively connected to a network including at least a second aerial vehicle, the computing device configured to: receive the external datum from the first sensor of the first aerial vehicle and the aircraft datum from the second sensor of the first aerial vehicle; and transmit at least a flight plan update element to the network based on the external datum and the aircraft datum.

Abstract: An electric aircraft for generating a yaw force includes a fuselage, a plurality of laterally extending elements secured to the fuselage, a plurality of lift components attached to the plurality of laterally extending elements, and at least a longitudinal thrust component attached to the plurality of laterally extending elements, wherein the longitudinal thrust component is configured to generate a yaw force.

Abstract: A system for establishing a primary function display for an electrical vertical takeoff and landing aircraft. The system further includes a plurality of sensors that detects at least a metric and generates at least a datum based on the at least a metric. Specifically, state of charge is at least generated based on the performance metric of an energy source. The system further includes a display to show the at least a datum. The system further includes a controller that receives the at least a datum and generates a visual to the pilot.

Abstract: Aspects relate to a system for flight plan generation of an electric vertical takeoff and landing (eVTOL) aircraft. An exemplary system for flight plan generation includes a flight controller mounted on an eVTOL aircraft. The flight controller may be configured to receive a plurality of flight plan data and generate a flight plan for the aircraft as a function of the plurality of flight plan data.

Abstract: An aircraft having reverse thrust capabilities, the aircraft includes a fuselage, a plurality of flight components configured to enable the aircraft at a low-speed flight mode, a pilot control, a sensor, an energy source, and a flight controller configured to receive the aircraft datum from the sensor at an initial time, wherein the initial time occurs when at least a flight component of the plurality of flight components produces a positive thrust, initiate a reverse thrust command as a function of the aircraft datum at a subsequent time wherein the reverse thrust command causes the at least a flight component of the plurality of flight components to produce a negative thrust, and the subsequent time occurs temporally after the initial time, and command the at least a flight component of the plurality of flight components to enter a speed reversal region.

Abstract: A system for estimating flight range of an electric aircraft. The system generally includes at least a sensor and a computing device. The at least a sensor is communicatively connected to at least a flight component. The at least a sensor is configured to detect a performance datum of the at least a flight component. The computing device is communicatively connected to the at least a sensor. The computing device is configured to receive the performance datum from the at least a sensor, determine an energy performance datum from the performance datum, determine a flight performance datum from the performance datum, generate a projected flight range datum as a function of the energy performance datum and the flight performance datum, and display the projected flight range datum. A method for estimating flight range of an electric aircraft is also provided.

Abstract: Braking systems and methods for an electrical vertical takeoff and landing aircraft are provided. A braking system may contain a pilot control device, brakes, wheels, sensors, and a controller. Pilot controls the pilot control device to transmit information to the controller such that the aircraft will slow down.

Abstract: A system for establishing a primary function display for an electrical vertical takeoff and landing aircraft. The system further includes a plurality of sensors that detects at least a metric and generates at least a datum based on the at least a metric. Specifically, state of charge is at least generated based on the performance metric of an energy source. The system further includes a display to show the at least a datum. The system further includes a controller that receives the at least a datum and generates a visual to the pilot.

Abstract: Aspects relate to a system for flight plan generation of an electric vertical takeoff and landing (eVTOL) aircraft. An exemplary system for flight plan generation includes a flight controller mounted on an eVTOL aircraft. The flight controller may be configured to receive a plurality of flight plan data and generate a flight plan for the aircraft as a function of the plurality of flight plan data.

Abstract: In an aspect of the present disclosure is a system of automated fleet management for aerial vehicles, including a first aerial vehicle, the aerial vehicle comprising: a first sensor configured to measure an external metric and generate external datum based on the external metric; and a second sensor configured to measure an aircraft metric and generate aircraft datum based on the aircraft metric; and a computing device operating on the first aerial vehicle, the computing device communicatively connected to a network including at least a second aerial vehicle, the computing device configured to: receive the external datum from the first sensor of the first aerial vehicle and the aircraft datum from the second sensor of the first aerial vehicle; and transmit at least a flight plan update element to the network based on the external datum and the aircraft datum.

Abstract: In an aspect of the present disclosure is a system for in-flight re-routing of an electric aircraft including a battery pack configured to provide electrical power to the electric aircraft; a sensor configured to detect at least a temperature metric of the battery pack and generate a temperature datum based on the at least a temperature metric; a controller communicatively connected to the sensor, the controller configured to: receive the temperature datum from the sensor; and re-route the electric aircraft based on the temperature datum.

Abstract: A system for aircraft recommendation for an electric aircraft is presented. The system includes a computing device, wherein the computing device is configured to, receive an aircraft datum, receive a flight plan, generate a model of at least a flight phase as a function of the aircraft datum and the flight plan, generate an aircraft recommendation as a function of the flight plan and aircraft datum, wherein generating the aircraft recommendation further comprise identifying a tunable parameter of the at least a flight phase, tuning the tunable parameter as a function of the model of the at least a flight phase and at least an objective constraint, and generating the aircraft recommendation as a function of the tuning. The system further includes a user device, wherein the user device is configured to display the aircraft recommendation.

Abstract: An aircraft having reverse thrust capabilities includes a fuselage, a plurality of flight components, a pilot control located within the fuselage, a sensor attached to the pilot control configured to detect an aircraft datum from the pilot control, and a flight controller, located within the fuselage, the flight controller configured to receive the aircraft datum from the sensor, and initiate a reverse torque command of a flight component of the plurality of flight components as a function of the aircraft datum.

Abstract: A system for in-flight stabilization including a plurality of flight components mechanically coupled to an aircraft, wherein the plurality of flight components includes a first flight component and a second flight component opposing the first flight component. The system further comprises a sensor mechanically coupled to the aircraft, wherein the sensor is configured to detect a failure event of a first flight component. The system comprises a vehicle controller communicatively connected to the sensor and is configured to receive the failure datum of the first flight component from the sensor, initiate an automatic response as a function of the failure datum. Initiating the automatic response further includes determining an autorotation inducement action for the second flight component to perform and commanding the second flight component to perform the autorotation inducement action.