Joby Aero, Inc.

Jason Ryan

JoeBen Bevirt

Alex Stoll

Gregor Veble Mikic

Scott MacAfee

Martin Van Der Geest

Rob Thodal

Jeremy Bain

Gregor Veble Mikić

Gregor Veble Miki

A vertical takeoff and landing aircraft includes a starboard wing, a port wing, first and second tilt rotors coupled to the port and starboard wings respectively, and first and second batteries. A pair of control surfaces are arranged on a first side of the mid-sagittal plane of the aircraft, the pair comprising a first and a second control surface. A first flight actuator is electrically connected to the first battery and a second flight actuator is electrically connected to the second battery. The first and second flight actuators are mechanically connected to the first and second control surfaces respectively.

Fault-tolerant VTOL aircraft with redundant control surfaces and actuators

A method for determining airspeed of an aircraft that includes determining a rotor model relating a power coefficient of a propeller of the aircraft to an axial inflow velocity through the propeller as a function of a set of rotor operating parameters; determining the set of rotor operating parameters by sampling an electronic control signal associated with an electric motor actuating the propeller; computing the axial inflow velocity through the propeller based on the set of rotor operating parameters using the rotor model; and determining the airspeed based on the axial inflow velocity.

System and method for airspeed determination

A system and method for reducing a psychoacoustic penalty of acoustic noise emitted by an aircraft, including a plurality of propulsion assemblies coupled to the aircraft, wherein each of the plurality of propulsion assemblies includes a motor, and a plurality of blades defined by a propeller, wherein the plurality of blades can define an asymmetric blade spacing; a control subsystem coupled to the aircraft and communicatively coupled to the motor of each of the plurality of propulsion assemblies, wherein the control subsystem is operable to rotate each of the plurality of propulsion assemblies at a different frequency to modulate the acoustic power distribution of the emitted acoustic signature.

System and method for aircraft noise mitigation

A power system with a reliability enhancing battery architecture for electric motors adapted for use in an aerial vehicle. Individual batteries may be used to power a subset two or more motors in systems with six or more motors, for example. Each motor may be powered by two or more subsets of batteries, allowing accommodation for motor failure. With a failed motor in a vertical take-off or landing mode, power may be diverted to other motors to continue proper attitude control, and to provide sufficient thrust. With a failed motor a second motor offset from the failed motor may be powered down to facilitate attitude control.

Electric power system architecture and fault tolerant VTOL aircraft using same

The power system can include: a plurality of batteries, a plurality of electric propulsion units, flight computers, and power connections. The propulsion assemblies can include a motor, a propeller, and one or more inverters. The power system can optionally include a plurality of flight actuators. However, the power system can include any other suitable set of components. The power system functions to provide aircraft propulsion and/or aircraft control authority during flight.

A power system with a reliability enhancing battery architecture for electric motors adapted for use in an aerial vehicle. Individual batteries may be used to power a subset two or more motors in systems with six or more motors, for example. Each motor may be powered may be powered by two or more subsets of batteries, allowing accommodation for motor failure. With a failed motor in a vertical take-off or landing mode, power may be diverted to other motors to continue proper attitude control, and to provide sufficient thrust. With a failed motor a second motor offset from the failed motor may be powered down to facilitate attitude control.

A fault-tolerant command and control system including a plurality of flight devices, a plurality of flight computers, a distribution network including a plurality of switches and cables connecting the plurality of flight devices to the plurality of flight computers, and a power source connected to the distribution network.

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Santa Cruz, CA, United States of America

Jason Ryan