Mimosa Networks, Inc.

Sifly Aviation, Inc.

Polycom, Inc.

2wire, Inc.

Airspan IP Holdco LLC

Western Gas and Electric Company

Hivespot, Inc.

Western Gas and Electric, Inc.

Brian L Hinman

Jaime Fink

Carlos Ramos

Mustafa Rangwala

David Gurevich

Vishakan Ponnampalam

Syed Aon Mujtaba

John R Sanford

Wayne H Miller

Justin Lee

Chiu Ngok Eric Wong

James T Schley-May

Hossein Kazemi

Muhammad Mubeen Javaid

Ashok N Masilamani

Miika Keskinen

Jeffrey C Rodman

Jeffrey G Bernstein

Paul Eberhardt

Scott H Wakefield

Pasquale Romano

Andrew L Norrell

Philip Stanley Bednarz

Ting Sun

Roeland Vandevelde

Eric K Gaut

Shan-Shan Huang

Daniel Harden

Arlie R Conner

Carl H Alelyunas

Paul Martell Trethewey

Philip G Baker

Frank Spiteri

Viggo Selchau-Hansen

Bryan K Brown

Andrew Norell

Tabetha L Hinman

Phil Frank

A rotor system for electrically powered rotorcraft is described, providing the benefits of fast thrust response, depending on rotor inertia. The rotor system includes a rotor hub and two or more rotor blades, and an electric motor driving the rotor hub. The rotor hub includes a mechanism which adapts the collective pitch of the rotor blades in response to the torque applied by the electric motor. When there is significant torque over a threshold, the rotor hub biases the blades to a higher collective pitch, which supports greater thrust, thus avoiding the lag in rotor thrust that would occur through RPM control.

Rotor system for electrically powered rotorcraft

Multi-band antenna arrays and methods of use are provided herein. An example device includes vertical surfaces arranged into a tubular configuration, where each of the vertical surfaces comprising antenna arrays is aligned along the vertical surfaces. The antenna elements are arrayed through a feed network in such a way that antenna gain is increased while elevation beam-width is reduced. The device also includes two or more radios connected to the antenna arrays on the vertical surfaces via the feed network.

Multi-band antenna array devices having a tubular configuration

Omni-directional orthogonally-polarized antenna system for MIMO applications are disclosed herein. An example antenna system comprises two arrays of horizontally polarized radiating elements, and two arrays of vertically polarized radiating elements, each array having roughly 180-degree radiation pattern, disposed about a central axis in a common horizontal plane, arrays of common polarization separated by 180-degrees. Also, the example antenna system includes at least one printed circuit board having a saw tooth pattern, wherein uniform coverage in both vertical and horizontal polarization over 360 degrees is provided using beamforming and polarization diversity.

Orthogonally-polarized antenna system and device for MIMO applications

Systems and methods of communication synchronization are described herein. An exemplary system includes two or more radios and a cloud controller. The two or more radios are collocated with one another and they communicate with two far radios over a pair of long range wireless links. The two or more radios are configured to transmit and receive in synchronization with one another on a same channel. An off-axis response for each of the two or more radios is reduced compared to their on-axis response for improved signal to noise ratio.

Systems and methods of communication synchronization between two or more radios

A system for landing and charging an autonomous unmanned aerial vehicle (UAV) is disclosed. The UAV comprises a set of battery powered rotors to fly through the air. The UAV further comprises a landing peg that projects beneath the body configured to be received by a socket of a corresponding landing base. The landing base can have a funnel top to make landing easier. The landing peg has a set of power transfer means that connect with power transfer means in the landing base to recharge the batteries of the UAV. The UAV can be guided to land in the landing base by a ring of LEDs on the landing base.

Autonomous unmanned aircraft system

A rotor system for electrically powered rotorcraft is described, providing the benefits of autorotation for safety, and fast thrust response, regardless of rotor inertia. The rotor system includes a rotor hub and two or more rotor blades, and an electric motor driving the rotor hub. The rotor hub includes a mechanism which adapts the collective incidence of the rotor blades in response to the torque applied by the electric motor. When there is little or no motor torque, the rotor hub holds the blades at a shallow incidence, which supports autorotative descent. During autorotative descent, the motor controller coupled to the electric motor utilizes electrical braking to moderate the rotor RPM and thrust. When the electric motor provides power to the rotor for normal flight, the collective blade incidence adjusts in response to the motor torque, providing a fast response in rotor thrust, thus avoiding the lag in rotor thrust that would occur through RPM control.

A method of operating an electrically powered rotorcraft of the type having a fuselage and a set of N rotors driven by a set of electric motors and coupled to the fuselage, N≥4, under a failure condition preventing ordinary operation of the rotorcraft. The method includes entering a failsafe mode of operation wherein autorotation of at least four of the rotors is enabled. The method also includes using electrical braking associated with a selected group of the rotors to control pitch, roll and yaw of the rotorcraft.

Rotorcraft autorotation control through electrical braking

An improved electrically powered rotorcraft is of the type having a rotor including a rotor hub and a pair of rotor blades mounted to the rotor hub on opposite sides thereof, the rotor being rotatably mounted on a primary drive shaft, and a rotary electric motor coupled to the drive shaft. In this rotorcraft, the improvement includes a common pitch-angle shaft coupled to each of the blades; a limited-angle electric motor, mechanically coupled to the common pitch-angle shaft, and configured to cause rotation of the common pitch angle shaft and therefore adjustment of pitch of the pair of rotor blades; and a controller system in communication with the limited-angle electric motor, configured to provide cyclic control of pitch of the pair of rotor blades.

Electric rotorcraft cyclic control system

Omni-directional orthogonally-polarized antenna system for MIMO applications are disclosed herein. An example antenna system can have two arrays of horizontally polarized radiating elements, and two arrays of vertically polarized radiating elements, each array having roughly 180-degree radiation pattern, disposed about a central axis in a common horizontal plane, arrays of common polarization separated by 180-degrees, such that MIMO processing of signals to the arrays of common polarization results in a radiation pattern that is substantially constant over 360-degrees in azimuth.

Omni-directional antenna system and device for MIMO applications

Simultaneous transmission on a shared channel by a plurality of collocated radios is provided herein. The two or more radios are collocated with one another and are communicating with two far radios over a pair of long range wireless links. The two or more radios are configured to transmit and receive in synchronization with one another on a same channel. An off-axis response for each of the two or more radios is reduced compared to their on-axis response for improved signal to noise ratio, and the on-axis response the two or more radios are substantially equal to one another.

Synchronized transmission on shared channel

A contra-rotating electric helicopter utilizes an electric motor having a base and an output shaft and a power source. The helicopter couples the base to a first rotor, thus allowing both the base and the power source to rotate within the frame of reference of the first rotor, while a contra-rotating and coplanar second rotor is coupled to the output shaft of the electric motor.

Contra-rotating electric helicopter

An improved vertical takeoff aircraft of the type having a set of pads that are in contact with the ground when the aircraft is at rest on the ground and a controllable lift and propulsion system. The aircraft includes an array of force sensors coupled to the set of pads. The array has an output providing measurements over time of forces exerted on the pads along at least two independent axes. The aircraft also includes a controller, coupled to the lift and propulsion system and to the array of force sensors. The controller is configured to control the lift and propulsion system in a manner to counteract forces exerted externally on the aircraft that would cause undesired motion of the aircraft when on the ground and transitioning from the ground to flight.

VTOL take-off control system

A method of operating an electrically powered rotorcraft of the type having a fuselage and a set of N rotors driven by a set of electric motors and coupled to the fuselage, N&#x2265;4, under a failure condition preventing ordinary operation of the rotorcraft. The method includes entering a failsafe mode of operation wherein autorotation of at least four of the rotors is enabled. The method also includes using electrical braking associated with a selected group of the rotors to control yaw of the rotorcraft.

Electrically powered rotorcraft capable of autorotative landing

WiFi repeater devices described provided herein. An example device includes an enclosure that is configured to be mounted to a window that divides an outdoor area from an indoor area. The enclosure houses a 5 GHz WiFi client radio coupled with a high order MIMO (multiple input, multiple output) antenna, the high order MIMO antenna transmitting and receiving data from a 5 GHz access point located in the outdoor area, and a 2.4 GHz WiFi access point radio coupled with a MIMO (multiple input, multiple output) antenna, the MIMO antenna transmitting and receiving data from 2.4 GHz UEs located in the indoor area.

Systems and methods of a Wi-Fi repeater device

Growing community of inventors

Los Gatos, CA, United States of America

Brian L Hinman