Beta Air, LLC

General Electric Company

Herman Wiegman

Kyle B Clark

Steven J Foland

Riley Clinton Griffin

Sean Richard Donovan

Braedon Andrew Lohe

Timothy Gerard Richter

David James

Sarah Kathleen Overfield

Irene Michelle Berry

Thomas Henck

Steven Willard Arms

Luis Jose Garces

Joshua E Auerbach

Donald Wayne Whisenhunt, Jr

Deepak Aravind

John Michael Kern

Stuart Denson Schreiber

Robert August Kaucic

Raffaello Verna

Mohammed Agamy

Peter Adam Gottlieb

Roger Neil Bull

Christopher James Chuah

Mark Edward Gotobed

Christopher J Woodall

Amit Raja Sanglikar

Augustus Brightman

Connor Brady

Kalyan Bukkasamudram

William Eugene Carlson

Anil Raj Duggal

Lembit Salasoo

Patrick Lee Jansen

Govardhan Ganireddy

Robert William Delmerico

Paul Robert Gemin

Ahmed Elasser

William Andrew Hennessy

Andrew Joseph Giroux

Vincent Moeykens

Kamron Mark Wright

Rui Zhou

Rajni Kant Burra

Mert Geveci

Ramanujam Ramabhadran

Alexander Hoekje List

Zhi Zhou

Charles Michael Stephens

David Charles Bogdan, Jr

Rayette Ann Fisher

Pradeep Vijayan

Richard Donnelly

Chaitanya Ashok Baone

Andrew William Berner

Lochie Ferrier

Nathan William Joseph Wiegman

Saijun Mao

Huiqing Wu

Naresh Acharya

Kenneth McClellan Rush

Martine A Rothblatt

Jiucai Zhang

Lukas Mercer Hansen

Qunjian Huang

Hullas Sehgal

Necip Doganaksoy

David L Churchill

Ajit Wasant Kane

Victor Robert Abate

Charles Clarence Hicks, Jr

Luca Tonini

Paul Michael Perozek

Chenjie Lin

Bansidhar Jagannath Phansalkar

Suyu Hou

Leng Mao

Sam T Liu

Gregory John Parker

Keith Andrew Longtin

Ying Mei

Zach Pan

Sunit Kumar Saxena

Monika Chawla

Bojan Djokanovic

Uday Prakashrao Mhaskar

Chester Stanley Jezierski

Dann Gwyn

Brian O Klinka

A system for initiating a command of an electric vertical take-off and landing (eVTOL) aircraft includes a flight controller configured to receive a topographical datum, receive a sensor datum from a sensor, identify an air position as a function of the sensor datum and the topographical datum, determine a command, including an actuator command, as a function of the identified air position and the determining of the command includes identifying at least one flight component of the eVTOL aircraft to be adjusted to perform the determined command, and initiate the command to adjust the identified flight component.

System and method for initiating a command of an electric aircraft

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.

Flight control system and method for an aircraft

Aspects relate to a charging port of an electric aircraft and methods of use terminating a charging connection between a charger and the electric aircraft. A charging port includes a controller that is configured to receive a control signal from a remote device and terminate the charging connection in response to the control signal.

Charging port of an electric aircraft

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.

System and methods for flight control for an electric aircraft

A system for controlling a flight boundary of an aircraft. The system includes a flight controller communicatively connected to the aircraft. The flight controller is configured to receive a plurality of flight data linked with the aircraft, determine a flight boundary for the aircraft as a function of the plurality of flight data, set an aircraft movement limit as a function of the flight boundary, receive a thrust envelope, and generate a control signal for the aircraft as a function of the aircraft movement limit and the thrust envelope. The control signal is limits the aircraft to remain within the flight boundary. A method for controlling a flight boundary of an aircraft is also provided.

Systems and methods for controlling a flight boundary of an aircraft

A distributed control system with supplemental attitude adjustment including an aircraft control having an engaged state and a disengaged state. The system also including a plurality of flight components and a plurality of aircraft components communicatively connected to the plurality of flight components, wherein each aircraft component is configured to receive an aircraft command and generate a response command directing the flight components as a function of supplemental attitude. The supplemental attitude based at least in part on the engagement datum and generating a supplemental attitude includes choosing a position supplemental attitude if the aircraft control is disengaged and choosing a velocity supplemental attitude if the aircraft control is engaged. In generating the response command, the aircraft attitude is combined with the supplemental attitude to obtain an aggregate attitude, and the aircraft component is configured to generate the response command based on the aggregate attitude.

Methods and systems for a distributed control system with supplemental attitude adjustment

A system for determining remaining useful energy in an electric aircraft, the system including a computing device where the computing device is configured to measure a internal state datum of a battery as a function of at least a sensor, receive the internal state datum from the at least a sensor, generate a useful energy remaining datum as a function of the internal state datum and a battery model, and display the useful energy remaining datum to a user.

Systems and methods for determining remaining useful energy in an aircraft

A system for emergency shutdown of an electric charger using a de-energizing protocol is presented. The system includes a computing device, wherein the computing device is configured to receive a sensor datum from a sensor, determine a disruption element between a charging connector and an electric vehicle as a function of the sensor datum, and initiate a de-energizing protocol as a function of the disruption element.

Systems and methods for emergency shutdown of an electric charger by a de-energizing protocol

An electric aircraft charging connector, including a direct current pin and/or an alternating current pin. The connector including a ground pin, the ground pin providing a grounded connection. The connector also including a resistance sensor, the resistance sensor electrically connected to the direct current pin and/or the alternating current pin, and the ground pin, the resistance sensor configured to measure a resistance datum, the resistance datum including: a first resistance, the first resistance comprising a measurement of resistance between the direct current pin and the ground pin; and a second resistance, the second resistance comprising a measurement of resistance between the alternating current pin and the ground pin. The connector also including a controller, the controller configured to: receive the resistance datum from the resistance sensor; and compare the resistance datum to a threshold resistance datum.

Systems and methods for a charging port of an electric vehicle

A system and method for the overcurrent protection in an electric vehicle is illustrated. The system comprises an electric vehicle charging port that includes an AC pin, a DC pin, a sensor, and a controller. The electric vehicle charging port also includes a protection circuit, wherein the protection circuit is configured to control a transmission of power through the electric vehicle charging port.

System and method for overcurrent protection in an electric vehicle

A system and method for managing residual energy in a charging component is disclosed herein. Managing residual energy includes detecting an electrical parameter of the charging component and the electrically connected battery pack and generating a residual datum. The residual datum is transmitted to a computing device. The computing device identifies a residual element, generates an alert datum, and executes a security measure.

System and method for managing residual energy in a charging component

In an aspect an apparatus for determining a most limiting parameter of an electric aircraft is presented. An apparatus includes at least a processor and a memory communicatively connected to the at least a processor. A memory contains instructions configuring at least a processor to receive aircraft data from a sensing device. A sensing device is configured to measure a parameter of an electric aircraft and generate aircraft data. At least a processor is configured to determine a most limiting parameter of an electric aircraft as a function of aircraft data. At least a processor is configured to communicate a most limiting parameter to a pilot indicator in communication with the at least a processor and memory communicatively connected to the at least a processor. A pilot indicator is configured to display a most limiting parameter to a user.

Apparatus for determining a most limiting parameter of an electric aircraft

The present invention is a system and methods for an immediate shutdown of charging for an electric vehicle charger. The system may include a sensor, which is communicatively connected to a charging connection, and a control circuit, which is communicatively connected to the sensor. If a disruption element is determined by the control circuit as a function of a charging datum of the sensor, then control circuit is configured to conduct an immediate shutdown of charger by disabling a communication of a charging connection to prevent harm to an electric vehicle, a charger, and/or a user.

System and methods for an immediate shutdown of charging for an electric aircraft

A system and method for landing an electric aircraft is provided. The system includes a controller, wherein the controller is communicatively connected to the sensor, wherein the controller is configured to, receive a plurality of measured flight data, determine a descent confirmation as a function of the plurality of measured flight data, generate a descent instruction set as a function of the descent confirmation and the plurality of measured flight data, wherein generating the descent instruction set further includes generating a transition instruction set, and transmit the descent instruction set to a plurality of flight components, wherein each flight component of the plurality of flight components are coupled to the electric aircraft.

Methods and systems for fixed wing flight to vertical wing flight for landing an aircraft

An apparatus for a ground-based battery management for an electric aircraft is presented. The apparatus includes a battery pack mechanically coupled to the electric aircraft, the battery pack includes at least a battery module that includes at least a battery unit that includes battery cells and a thermal conduit configured to transfer heat between the battery cells and the thermal conduit and a thermal circuit mechanically coupled to the thermal conduit configured to facilitate the heat transfer using thermal media. The apparatus includes a media channel communicatively connected to a computing device and comprising at least a sensor, wherein the media channel is configured to evacuate the thermal media out of the battery pack using the thermal circuit and the computing device that includes a battery management system is configured to receive a condition parameter as a function of the at least a sensor of the media channel.

Apparatus for a ground-based battery management for an electric aircraft

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Essex Junction, VT, United States of America

Herman Wiegman