Joby Aero, Inc.

Joby Photo, Inc.

Gopro, Inc.

Day Men Us, Inc

Other

Joby Aviation, Inc.

Motrr LLC

Mixt Beverages, Inc.

Joby, Inc.

JoeBen Bevirt

Alex Stoll

Gregor Veble Mikic

Jason Ryan

Edward Stilson

Rob Thodal

Ernest Matthew Villanueva

Jonathan Wagner

Austin Lawrence Newman

Josh Guyot

Jeremy Bain

Brian Uznanski

Nathaniel Martin

Kevin Witt

Scott MacAfee

Martin Van Der Geest

Joey Milia

Gregor Veble Mikić

Benjamin John Brelje

Vishnu Vithala

Robert Gulliver Lynn

Kevin O'Connor

Joachim L Grenestedt

Blake W English

Robert Thodal

Michael Burghardt

Percy Pei

Pranay Sinha

Drew Boggio

Kyle Cordes

Tianyu Gu

Daniel Burghardt

Fred Italo Polito

David Eliot Scheinman

Baixi Pei

Steven Waller

Jordin Gischler

David D Craig

Peter Frykman

Matthew Peddie

Jeffrey K Gibboney

Gregory Cole DiMaggio

Alec Morgan Clark

Andy Clark

Steve Waller

Gregor Veble Miki

An aircraft propulsion system with an internally cooled electric motor adapted for use in an aerial vehicle. The motor may have its stator towards the center and have an external rotor. The rotor structure may be air cooled and may be a complex structure with an internal lattice adapted for airflow. The stator structure may be liquid cooled and may be a complex structure with an internal lattice adapted for liquid to flow through. A fluid pump may pump a liquid coolant through non-rotating portions of the motor stator and then through heat exchangers cooled in part by air which has flowed through the rotating portions of the motor rotor. The drag reduction portion and the cooled electric motor portion may share the same inlet.

Aircraft electric motor cooling system

An aircraft including an airframe and a plurality of propulsion assemblies coupled to the airframe, wherein each propulsion assembly includes an electric motor, a propeller coupled to the electric motor, and a tilt mechanism that connects the propulsion assembly to the airframe and transforms the propulsion assembly between a forward configuration and a hover configuration; wherein the plurality of propulsion assemblies is transformable between a forward arrangement and a hover arrangement, wherein each of the plurality of propulsion assemblies is in the forward configuration in the forward arrangement, wherein each of the plurality of propulsion assemblies is in the hover configuration in the hover arrangement, wherein the spacing between at least two of the propellers of the plurality of propulsion assemblies changes between the forward arrangement and the hover arrangement.

Electric tiltrotor aircraft

A multi-segment oblique flying wing aircraft which has three distinct segments including two outer wing segments and a central wing segment. The central segment may be thicker in the vertical direction and adapted to hold pilots and passengers. The outer wing segments may be substantially thinner and may taper as they progress outboard from the wing center. The multi-segment oblique flying wing aircraft be adapted for rotating into a high speed flight configuration, or may be adapted for take-off and cruise at a constant angle. In an extreme flight case, the central wing segment may rotate to a local sweep of ninety degrees.

Multi-segment oblique flying wing aircraft

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 method and system for modeling aerodynamic interactions in complex eVTOL configurations for realtime flight simulations and hardware testing which includes decomposing the aircraft into aerodynamic subcomponents, wherein the interactions between these components are handled by flow simulations of the surrounding fluid, which may be Euler flow CFD simulations. The system may be used as a flight simulator for pilot training in a realtime environment. The system may be used to support component testing using an interface to those components, such as flight electronics and actuators, to test the components in high fidelity simulations of actual flight demands on those components. The system may also be used to support design analysis in non-realtime to run numerous simulations on different designs and to provide comparative output.

Realtime flight simulation using method and system for modeling aerodynamic interactions in complex eVTOL configurations

An oblique flying wing aircraft with internal ducting and airflow. The aircraft may have propulsion units within the wing body. The propulsion units may be off-axis internal to the wing to utilize locations with larger internal space available. In some aspects, the multi-segment oblique flying wing aircraft may have three distinct segments including two outer wing segments and a central wing segment. The central segment may be thicker in the vertical direction and adapted to hold pilots and passengers. The outer wing segments may be substantially thinner and may taper as they progress outboard from the wing center. The multi-segment oblique flying wing aircraft be adapted for rotating into a high-speed flight configuration, or may be adapted for take-off and cruise at a constant angle.

Oblique flying wing aircraft with internal ducting and internal propulsion

A vertical take-off and landing aircraft with a multi-element lifting system with integrated propulsion. The multi-element lifting system may have an upper wing element, a lower wing element, and a control wing element which is located below the upper wing element and above, and rearward of, the lower wing element. The system uses internal propulsion units, such as internal ducted fans, which flow air below the upper wing element and above the lower wing element such that the air flows through the multi-element lifting system. The control wing element may be articulated to route air vertically downward to allow for short or vertical take-off and landing. An aircraft with a multi-element wing assembly and a multi-element tail assembly raised above the wing assembly. An aircraft which resides on the ground with the wing assembly and the tail assembly pitched up.

Multi-element lifting system with integrated propulsion and aircraft using same

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

The system can include an on-board thermal management subsystem. The systemcan optionally include an off-board (extravehicular) infrastructure subsystem. The on-board thermal management subsystem can include: a battery pack, one or more fluid loops, and an air manifold. The systemcan additionally or alternatively include any other suitable components.

Vehicle cabin thermal management system and method

A deployment mechanism for use on an aerial vehicle adapted for vertical takeoff and landing using deployable thrust producing elements for takeoff and landing. The deployment mechanism may use linear actuation of a linkage assembly to deploy thrust producing rotor assemblies from a vertical thrust hove configuration to a horizontal thrust forward flight configuration. The aerial vehicle may include left side rotor assemblies and right side rotor assemblies which may be deployed by deployment mechanisms.

Rotor deployment mechanism for vertical take-off and landing aircraft

A vertical take-off and landing aircraft which uses fixed rotors for both VTOL and forward flight operations. The wing rotors are tilted forward and provide some forward propulsion during horizontal flight. The rotors are positioned to achieve a high span efficiency. The rotors are positioned to even out the lift across the span of the synthetic wing. The synthetic wing may also have airfoils which may provide structural support for the rotors as well as providing lift during forward flight.

Method for flying VTOL aircraft with forward canted rotors

A vertical take-off and landing aircraft and method which uses fixed rotors for both VTOL and forward flight operations. The rotors are positioned to achieve a high span efficiency. The rotors are positioned to even out the lift across the span of the wing. The wing may also have narrow front and rear airfoils which may provide structural support as well as providing lift during forward flight, or may have a single center wing. The wing rotors are tilted forward and provide some forward propulsion during horizontal flight.

VTOL aircraft using fixed forward canted rotors

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

A high efficiency hydrogen fuel system for an aircraft at high altitude which utilizes compressors to compress air to a sufficiently high pressure for the fuel cell. Liquid hydrogen is compressed and then utilized in heat exchangers to cool the compressed air, maintaining the air at a temperature low enough for the fuel cell. The hydrogen is also used to cool the fuel cell as it is also depressurized prior to its entry in the fuel cell cycle. A water condensation system allows for water removal from the airstream to reduce impacts to the atmosphere. The hydrogen fuel system may be used with VTOL aircraft, which may allow them to fly at higher elevations. The hydrogen fuel system may be used with other subsonic and supersonic aircraft, such as with asymmetric wing aircraft.

High efficiency hydrogen fueled high altitude thermodynamic fuel cell system and aircraft using same

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Santa Cruz, CA, United States of America

JoeBen Bevirt