Archer Aviation, Inc.

Nathan Thomas Depenbusch

Geoffrey C Bower

Jeffery Scott Greenwood

Nansi Xue

Alan Chen

Benjamin Goldman

John Melack

Jenner Grey Richards

Fernanda Aline Matta De Paiva

Jeffrey Mark Bosworth

Ricardo Augusto Marques

Nathan Paul Pringle

Benjamin M Greek

Sang Gyun Park

Aspects of the present disclosure generally relate to systems and methods for flight control of aircrafts driven by electric propulsion systems and in other types of vehicles. In some embodiments, a computer-implemented method for command prioritization in an aircraft is disclosed. The method comprises receiving a pilot command, analyzing the pilot command to determine characteristics associated with the pilot command, wherein the characteristics to airspeed and climb of an aircraft, assigning weights to characteristics associated with the pilot command based on constraint data, determining priority of execution between airspeed and climb based on the weights assigned to the characteristics associated with the pilot command, calculating a correction factor to be applied to the characteristics associated with the pilot command based on determined priority and generating at least one actuator command to control the aircraft based on determined priority of execution.

Systems and methods for aircraft function prioritization and allocation

A method of controlling an electric aircraft that has a plurality of actuators that includes a plurality of electric propulsion units includes: receiving force and moment commands for the electric aircraft; determining control commands for the plurality of actuators based on the desired force and moment commands by solving an optimization problem that comprises a noise minimization term for minimizing noise generated by the electric propulsion units; and controlling the plurality of actuators according to the determined control commands to meet the force and moment commands for the electric aircraft.

Systems and methods for control allocation for electric vertical take-off and landing aircraft

Aspects of the present disclosure generally relate to systems and methods for flight control of aircrafts driven by electric propulsion systems and in other types of vehicles. In some embodiments, a flight control system of an aircraft is disclosed, configured to receive one or more signals to control movement of the aircraft, determine at least one flight condition of the aircraft, wherein the at least one flight condition includes at least a phase of flight, calculate at least one or more loads associated with the aircraft based on the determined at least one flight condition; determine an optimized flight configuration to alleviate loads on one or more components of the aircraft based on the received one or more signals and the calculated loads, generate one or more effector commands based on the optimized flight configuration; and actuate one or more aircraft effectors based on the one or more effector commands.

Systems and methods for aircraft load alleviation

A control system for a powered lift aircraft includes a pilot input device, at least one powered lift element configured to provide powered lift support to the aircraft, and a processor. The processor is configured to receive, from the pilot input device, an input indicative of one of a powered lift enabled mode or a powered lift disabled mode and control the at least one powered lift element to operate the aircraft in a selected one of the powered lift enabled mode or the powered lift disabled mode based on the received input. When the aircraft is in the powered lift enabled mode, the at least one processor is configured to control the at least one powered lift element based on a state of the aircraft. When the aircraft is in the powered lift disabled mode, the at least one processor is configured to control the at least one powered lift element to disable powered lift.

Powered lift enable and disable switch

Disclosed are systems and methods for controlling an electric vertical take-off and landing (eVTOL) aircraft. In one embodiment, a system comprises a processor, a first inceptor, communicatively coupled to the processor, the first inceptor configured to accept longitudinal and lateral linear movements as manual input and provide corresponding signals to the processor, and a second inceptor, communicatively coupled to the processor, the second inceptor configured to accept longitudinal and lateral linear movements as manual input and provide corresponding signals to the processor, wherein the processor is configured to control a heading of an aircraft using a signal received from the second inceptor corresponding to lateral linear movement of the second inceptor. Some embodiments may additionally include at least one sensor and a thumb stick for each inceptor.

Systems and methods for simulating an electric vertical take-off and landing aircraft

Systems and methods for controlling an electric vertical take-off and landing aircraft

An electric aircraft includes rotors for providing lift for vertical take-off and landing of the aircraft, proprotors that are tiltable between lift configurations for providing lift for vertical take-off and landing of the aircraft and propulsion configurations for providing forward thrust to the aircraft, a first battery pack for powering a first rotor and a first proprotor, a second battery pack for powering a second rotor and a second proprotor, a first electric power bus electrically connecting the first battery pack to the first rotor and proprotor, and a second electric power bus electrically connecting the second battery pack to the second rotor and proprotor, wherein the second electric power bus is electrically isolated from the first electric power bus.

Growing community of inventors

Mountain View, CA, United States of America

Nathan Thomas Depenbusch