Beta Air, LLC

Lochie Ferrier

Riley Clinton Griffin

Nicholas Moy

Collin Freiheit

John Charles Palombini

Steven J Foland

Alexander Hoekje List

Nick Warren

Herman Wiegman

Nathan William Joseph Wiegman

Nicholas Granger Warren

Herman Lucas Norbert Wiegman

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.

Aircraft having reverse thrust capabilities

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.

Methods and system for estimating percentage torque produced by a propulsor configured for use in an electric aircraft

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, generate a failure notification configured to indicate that the vehicle controller received the failure datum from the sensor, and 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.

In-flight stabilization of an aircraft

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.

Systems and methods for automated fleet management for aerial vehicles

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.

Electric aircraft for generating a yaw force

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.

System for establishing a primary function display in an electrical vertical takeoff and landing aircraft

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.

System for flight plan generation of an electric vertical takeoff and landing (eVTOL) aircraft and a method for its use

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.

Systems and methods for an electric vertical takeoff and landing aircraft braking system

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.

System and method for aircraft recommendation for an electric aircraft

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.

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.

Aspects relate to systems and methods for orienting a thrust propulsor in response to a failure event of a vertical take-off and landing (VTOL) aircraft. An exemplary system includes a plurality of lift propulsors mechanically connected to a VTOL aircraft, wherein each of the plurality of lift propulsors are configured to produce lift, a plurality of sensors, wherein at least a sensor is configured to detect a failure of at least a lift propulsor, and transmit a failure datum, a thrust propulsor mechanically attached to the VTOL aircraft with an orientable joint, wherein the thrust propulsor is configured to produce thrust and orient the thrust propulsor as a function of a thrust orientation datum, and a flight controller configured to receive the failure datum, generate a thrust orientation datum as a function of the failure datum, and transmit the thrust orientation datum to the orientable joint.

Methods and systems for orienting a thrust propulsor in response to a failure event of a vertical take-off and landing aircraft

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.

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Sydney, Australia

Lochie Ferrier