The Boeing Company

Theboeing Company

Brian Jay Tillotson

Charles Briggs Spinelli

Tamaira Emily Ross

Peng Zeng

Kevin Yong Ung

Chris B Kettering

James T Farricker

William Peck Pflug

Bradley James Mitchell

Michael Steven Lewis

Steven Craig Venema

Michael J Dunn

David B Blackwell

Daniel A Hendricks

Jere S Meserole, Jr

Brenda K Carlson

Peter E Herley

Richard R Rocks

David Arthur Whelan

John Lyle Vian

Dan John Clingman

Robert Paul Higgins

Carol Elizabeth Anway

Phillip R Rotta

Michael Chih-Huan Wang

Andrej Martin Savol

Keith J Glover

Bronwyn A Jackson

Michael A Loudiana

Jeffrey Evan Hanneman

Jay S Pearlman

Zach J Harris

Janice D Houston

Anat Bordoley

Arun Ayyagari

Robert Pierce Lutter

George Michael Roe

Craig Farris Battles

Larry P Torre

Gregory A Kimberly

Kenneth A Cobleigh

Joshua Przybylko

Brian Gregory Fischer

Marissa K Singleton

Kathryn Mary Neville

Alyson Bonk

Bailey Keakulina Eaton

Christopher Higgs

Jeffery D Musiak

Steven Richard Corey

Kerri L Olson

Jennifer K Baerny

Kristina A Chinn

Steven C Venema

Brian G Fischer

Jeffrey E Hanneman

Tamaira Ross

Marissa Singleton

Kathryn M Neville

Tamaira E Ross

Chris Kettering

Systems and methods for transferring electric power to an aircraft during flight. Power transfer to the receiver aircraft is effected by means of a donor aircraft using a wired electrical connection. The method for transferring electric power includes: establishing an electrical connection between a receiver aircraft and a donor aircraft during flight; and transferring electric power from the donor aircraft to the receiver aircraft via the electrical connection. In one embodiment, electric power is transferred by way of a power cable deployed by the donor aircraft, a drogue attached to a trailing end of the power cable, and a probe mounted to the fuselage of the receiver aircraft, The probe and drogue are configured to form an electrical connection when fully engaged.

Systems and methods for transferring electric power to an aircraft during flight

A system for inspecting a wire segment includes an inspection apparatus and a visual imaging device. The apparatus includes an array of mirrors positioned about a centerline of the apparatus, wherein each mirror in the array is oriented such that a reflection of a first inspection zone of the wire segment in the array of mirrors forms a circumferential view of the first inspection zone of the wire segment, and the reflection from each mirror is within a field of view from a single vantage point. The visual imaging device is positioned at the single vantage point and oriented towards the wire segment such that the reflection from each mirror of the array of mirrors is within a field of view of the visual imaging device, the visual imaging device configured to capture at least one image of the reflection of the wire segment from the array of mirrors.

Apparatus and methods of inspecting a wire segment

A transmitter for providing energy to a beam-powered aircraft includes an energy source that outputs an energy beam having an elongated cross-section, and a mount. The mount is operable to vary an azimuth and an elevation of the energy beam, and operable to rotate the energy beam about a central axis of the energy beam.

Beamed power system and method

A method of measuring air data of an aircraft is provided. The method includes emitting, by a laser disposed on the aircraft, laser light into air outside the aircraft, the laser tuned to induce a laser-induced plasma channel (LIPC) in the air. The method also includes sensing, by a sensor system disposed on the aircraft, at least one property of the LIPC. The method further includes computing, by a computing device disposed on the aircraft, the air data of the aircraft based on the at least one property of the LIPC.

Method and system for collecting air data using a laser-induced plasma channel

Provided are various spacecraft propulsion systems, and associated methods of operation. A spacecraft comprises an ion propulsion system and an ion blocker suspended from the spacecraft via one or more electrically insulated tethers. The ion propulsion system is configured to generate a first propulsive force by emitting a charged ion beam in a direction with an ion velocity vector comprising an ion vector component that is perpendicular to a magnetic field of a planet, such as Earth. The magnetic field causes the ion beam to curve toward the ion blocker at a trajectory such that ions within the ion beam are blocked by the ion blocker to generate a second propulsive force on the ion blocker. The ion blocker blocks the ions by contacting or deflecting the ions. The ion blocker is positioned approximately twice the gyroradius of the ion beam trajectory.

Enhanced thrust from ion-propelled spacecraft via tethered ion blocker

An example method includes determining, by a flight planning system, a perceived noise at a surface location based on acoustic noise emitted by an aerial vehicle at an aerial location. The aerial location corresponds to a waypoint along a proposed trajectory. Further, determining the perceived noise includes estimating propagation of the acoustic noise from the aerial location to the surface location based on environmental features of the environment or weather data. The flight planning method also includes determining, by the flight planning system using a noise-abatement function, a noise-abatement value of the proposed trajectory for the aerial vehicle based on the perceived noise at the surface location. In addition, the flight planning method includes determining, by the flight planning system, a flight plan for the aerial vehicle based on the noise-abatement value of the proposed trajectory, and outputting the flight plan for use in navigating the aerial vehicle.

Community noise abatement in dynamic environment

A device to remove moisture from air. The device includes a container with an interior space that contains liquid saline solution. The interior space is configured to prevent the saline solution from escaping into the environment. A saline solution moving device moves the saline solution within the interior space. An air moving device moves air through the interior space. The movement of the air within the interior space exposes the air to the saline solution and enables moisture within the air to be absorbed into the saline solution.

Humidity control via saline solution circulation

Systems, methods, and apparatus for magnetic maneuvering for satellites are disclosed. In one or more embodiments, a method for maneuvering satellites comprises applying, by a current source in a first satellite, current to an electromagnet in the first satellite. The method further comprises generating, by the electromagnet in the first satellite in response to the current, a magnetic field. Further, the method comprises maneuvering, by the first satellite, a second satellite via the magnetic field. In one or more embodiments, the electromagnet comprises a torque rod, an electric motor coil, and/or a solar array. In one or more embodiments, the second satellite comprises a ferromagnetic or ferrimagnetic material, a conductive material, or a combination thereof. In some embodiments, the second satellite comprises an electromagnet.

Magnetic maneuvering for satellites

An apparatus for use in inspecting a wire segment is provided. The apparatus includes a guide tube sized to receive the wire segment, and an array of mirrors positioned about the guide tube. Each mirror in the array is oriented such that a reflection of the wire segment in the array of mirrors forms a circumferential view of at least a portion of the wire segment, and such that the reflection from each mirror is within a field of view from a single vantage point.

An electrode-arc sensor for measuring air data. The sensor includes a pair of electrodes which are arranged substantially parallel to one another to form a fluid gap therebetween. The fluid gap is arranged to receive a stream of fluid such as air. A voltage source is operatively connected to the pair of electrodes to generate a voltage and induce an arc therebetween. A controller operatively connected to the voltage source is configured to command the voltage source to generate a voltage until the arc is induced. Once induced, a time-series of the voltage measurements is generated based on a voltage sensor across the pair of electrodes. The ionized air surrounding the induced arc is acted upon by the fluid stream. The controller determines a fluid speed and fluid density of the fluid stream based on the time series of voltage measurement as the arc travels past the pair of electrodes.

Electrode-arc sensor air data system for an aircraft

An eddy current system and methods of performing operations on a structure using the eddy current system are presented. The eddy current system comprises an ion beam source and a magnetic field source with at least one of variable output intensity or variable output orientation.

Eddy current system for use with electrically-insulative structures and methods for inductively heating or inductively inspecting

A spacecraft includes a body defining an interior payload region and a particle dispersion layer disposed between the interior payload region and one or more exterior surfaces of the body. The particle dispersion layer is formed of one or more magnets having a persistent magnetic field. The spacecraft including the particle dispersion layer may be manufactured by obtaining a particle dispersion layer having a persistent magnetic field, identifying a directionality of the persistent magnetic field of the particle dispersion layer, and installing the particle dispersion layer between an interior payload region formed by a body of a spacecraft and one or more exterior surfaces of the body according to the identified directionality of the persistent magnetic field.

Particle dispersion layer having persistent magnetic field

Methods and systems according to one or more examples are provided for avoiding foreign object strikes on rotorcraft vehicles. In one example, a vehicle comprises a rotor comprising a rotor blade, a first sensor configured to provide first sensor information associated with an object proximate the vehicle, and a second sensor configured to provide second sensor information associated with the rotor. The vehicle further comprises a processor coupled to the first sensor and the second sensor configured to selectively control the rotor to minimize damage to the vehicle by the object based on the first and second sensor information.

Systems and methods for avoiding strikes on multi-rotor vehicles

A radioisotope power source is disclosed. In one embodiment, the power source includes a dielectric liquid held within a vessel, a radioisotope material dissolved as an ionic salt within the dielectric liquid thereby forming an ionic salt solution, and a thermal-to-electric power conversion system configured to receive thermal heat generated from the decay of the radioisotope material and to generate electrical power.

Radioisotope power source

Growing community of inventors

Seattle, WA, United States of America

Brian Jay Tillotson