The Boeing Company

James C Russell

Kevin Scott Callahan

Timothy R North

Daniel J Murray

Vyacheslav Khozikov

Thomas P Barrera

Douglas Dean Maben

Kelly Thomas Jones

Kyle Masao Nakamoto

John Rubrecht Lowell

Bruce Lee Drolen

Frederic Lacaux

Landon Keith Henson

Charles Otis Adler

Daniel F Lewinski

Richard Kevin Johnson

Michael L Trent

Royal E Boggs

Mehdy Barekatein

Mark E Smith

George A McEachen

Julie K Plessner

Nels A Olson

Bruce L Drolen

Jean-Philippe Belieres

Richard P Lorenz

Alan D Amort

Harry H Ayubi

Mohammad M Malik

Matthew J O'Brien

David C Shangraw

Thomas A Jessett

Ramon L Cuenca

Fadl I Khalil

Alfred R Carlo

Scott B Vacknitz

Collis M Walker

Warren S Ng

Archibald A Gray

Shellini P Dowell

Craig G Robotham

Michael R Madden

Pazion Cherinet

Bryan Shiflett

Scott Wadley

Tresha L White

Carol Barnhart

Frederic P Lacaux

Matthew J O'brien

George A Mceachen

Nels S Olson

John R Lowell

Douglas D Maben

Richard K Johnson

Kelly T Jones

Kevin S Callahan

An avionics unit assembly for an aircraft can include an avionics unit (e.g., an underwater locator device, 'ULD'), and a battery to power the avionics unit. The avionics unit assembly can further include a housing that encases the avionics unit and the battery. The housing includes a vent port for exhausting an emission from the housing during a failure of the avionics unit. The avionics unit assembly can further include one or more of a suppressor that filters the emission, a shield element that is resistant to chemical and/or thermal effects of the emission, and a bracket for mounting the avionics unit to a surface. A method integrating the avionics unit assembly onto a forward aircraft bulkhead at a mount location under an aircraft radome and for manufacturing the avionics unit, and an aircraft including the avionics unit are also described.

Behind the radome mounting system for aircraft avionics equipment

There is provided an oriented wire electrostatic radiation protection system for a spacecraft. The system has a wire management system, and first and second wires coupled to the wire management system. A first wire orientation apparatus orients the first wire in a first wire direction toward, and in parallel alignment with, an approach path of approaching solar particles. A second wire orientation apparatus orients the second wire in a second wire direction opposite to the first wire direction. The system has a control system, and a power supply to charge the first wire to a positively-charged wire and to charge the second wire to a negatively-charged wire. When the approaching solar particles travel alongside the positively-charged wire toward the spacecraft, the positively-charged wire deflects the approaching solar particles away from the spacecraft, via electrostatic repulsion, and the positively-charged wire creates a radiation protection shielded region around the spacecraft.

Oriented wire electrostatic radiation protection system and method for spacecraft

An avionics unit assembly for an aircraft includes an avionics unit such as an underwater locator device (ULD) having a transmitter configured to output a radio frequency pulse and a battery configured to power the device. The avionics unit assembly can further include a housing that encases the transmitter and the battery and includes a vent port for exhausting an emission from the housing during a failure of the avionics unit. The avionics unit assembly can further include one or more of a suppressor that filters the emission, a shield element that is resistant to chemical and/or thermal effects of the emission, and a bracket for mounting the avionics unit assembly to a surface. The suppressor can include a plurality of channels, where each channel includes at least one blind alley that can capture/filter a particulate component and/or a liquid component from the emission and/or break up the particulate component.

Underwater locator device (ULD) particle suppressor/trap

A rechargeable battery comprises a chassis including a lower fixation plate, and a plurality of battery cells on the lower fixation plate. The lower fixation plate includes at least one flow channel positioned to collect condensate from the battery cells and move the collected condensate away from the battery cells.

Chassis for rechargeable battery

A rechargeable battery comprises a plurality of individual sealed battery cells, and dielectric separators between the battery cells for creating thermal barriers between opposing surfaces of the battery cells. The dielectric separators are made of a fiber composite.

Rechargeable battery including battery cell separators

An aircraft comprises a rechargeable battery including an array of battery cells, and means for mitigating consequences of failure of the rechargeable battery due to aircraft operating cycles.

Aircraft including mitigation system for rechargeable batteries

A system and methods for magnetically managing combustion are presented. Fuel is injected into a magnetic field at least partially enclosed in a combustion chamber, and a combustion region comprising electrically conductive species is produced by combusting the fuel. The combustion region is magnetically controlled using the magnetic field operating on the electrically conductive species.

Magnetically managed combustion

An interferometer, preferably a wedge etalon, produces a spatial pattern of fringes when incident radiant energy is coherent. A system for analyzing these fringes uses a transform operation to detect spatial regularity. The transform operation may be electronic (computational) based on the output of individual photodetectors of an array disposed adjacent to the interferometer, or optical by a Fourier transform lens disposed adjacent to the interferometer. In either case, the combination of fringe creating element and transform operation permits the unambiguous detection of light with a coherence length longer than that of natural light, such as from a laser.

Coherent laser warning system

Three-layer light guide transports light from a source of low aspect ratio (e.g. nearly circular or nearly square) to one of high aspect ratio (e.g. narrow slit) to produce an output beam of low output divergence angles at high transfer efficiency. The design principle eliminates tapers or bends in the guide surfaces. Thereby, light from a conventional round lamp may be redirected with high optical efficiency to an aperture constrained to a long, narrow area, as in a slit headlight, a nacelle-rim light, a radome-edge light, or a landing light embedded in a wing having a sharp leading edge. The resulting far field intensity pattern is similar to that of a conventional sealed beam lamp.

Trilaminar dual reflex light guide

Growing community of inventors

Bellevue, WA, United States of America

James C Russell