Archer Aviation, Inc.

Geoffrey C Bower

Spencer Fugal

Giovanni Droandi

Julien Thiebaud

Julien Montousse

Erik Saetre

Niki James Smart

Nicolas Rousseau

Young-Joon Suh

Dev Gorur Rajnarayan

Nathan Thomas Depenbusch

Jenner Grey Richards

Alexander Oliver Haas

Nischint Rajmohan

Bernardo Augusto De Oliveira Vieira

Christopher M Heath

Nansi Xue

Benjamin Goldman

Alan Chen

Pieter Depape

John Melack

Guy Bernard

Stephen Michael Spiteri

Kurt James Wagner

Diederik Marius

Pedro Roberto Paterson Carleial

Paul Frihauf

Fernanda Aline Matta De Paiva

Jeffery Scott Greenwood

Alex Clarabut

Saienath Poopalarajah

Katarina Alexis Morowsky

Joao Paulo Marques Reginato

Ricardo Augusto Marques

Benjamin M Greek

Alexander Stephen Ostrow

Adam Goldstein

Robert Alan Ng

Sai Poopalarajah

Devesh Jain

A rotor mounting assembly for a vertical take-off and landing aircraft includes a boom configured for mounting to a wing of the aircraft; a mount for mounting a rotor assembly, the mount connected to the boom at a joint and tiltable about the joint from a forward thrust orientation in which the rotor assembly can provide forward thrust for forward flight to a vertical thrust orientation in which the rotor assembly can provide vertical thrust for vertical take-off and landing and hover; a multi-link assembly extending from the boom to the mount; and a rotary actuator for actuating the multi-link assembly to control tilting of the mount.

Systems and methods for controlling rotor tilt for a vertical take-off and landing aircraft

A vertical take-off and landing aircraft may include a fuselage; at least one wing connected to the fuselage; a first plurality of proprotors mounted to the at least one wing, positioned at least partially forward of a leading edge of the at least one wing, and 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; and a second plurality of proprotors mounted to the at least one wing, positioned at least partially rearward of a trailing edge of the at least one wing, and 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; wherein the first plurality of proprotors and the second plurality of proprotors are independently tiltable.

Vertical take-off and landing aircraft with AFT rotor tilting

The present disclosure relates generally to controlling an aircraft to avoid overheating components. In one embodiment, a method is disclosed, comprising: receiving first sensor data indicating at least one attribute of high voltage wiring of the aircraft; receiving a state of operation of the aircraft; determining a proximity of a temperature of the high voltage wiring to a temperature limit based on the first sensor data and the state of operation of the aircraft; and controlling at least one electric propulsion unit of the aircraft to avoid exceeding the temperature limit based on the determined proximity.

Systems and methods for thermal management of high voltage wiring in an aircraft

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

Aircraft

An aircraft system for damping movement of a structural flight element. The aircraft system including a moveable aircraft structure, a power source, a controller, a resistor, and a first transistor connected in series to the resistor. When the power source of the aircraft is providing power, the controller controls the first transistor to prevent current flow through its terminals and through the resistor. Further, when the power source of the aircraft is not providing power, the first transistor allows current generated by a back EMF (electromotive force) voltage to flow through its terminals and through the resistor, the back EMF voltage being created by movement of the moveable aircraft structure.

Systems and methods for electric damping of aircraft flight control surfaces and propellers

Display screen with animated avionics graphical user interface

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

Vertical take-off and landing aircraft with aft rotor tilting

Growing community of inventors

Sunnyvale, CA, United States of America

Geoffrey C Bower