The Boeing Company

Michael K Klein

Christopher E Plass

Kevin Scott Callahan

Jamie J Childress

Douglas Alan Brown

Steven Paul Walker

Arthur Edward Brockschmidt, Jr

Teresa A King

Frederick Theodore Calkins

Yakentim M Ibrahim

James Henry Mabe

Gregory M Santini

Stephen Roger Amorosi

Adriana Willempje Blom

Michael Albert Balzer

John A Standley

Henry John Koppelman

Randall L Mosten

Flint Matthew Jamison

Charuhas M Soman

Paula Jo Boppre

Brian Montague

John V Salmi

Christopher H Abada

Flint M Jamison

A sanitizing system and method include a sanitizing head including an ultraviolet (UV) lamp, and a cooling manifold configured to deliver air to the UV lamp. The sanitizing system can also include an exhaust sub-system.

Systems and methods for cooling ultraviolet (UV) lamps

A portable sanitizing method includes moving a cover of a case assembly between an open position that exposes a storage chamber and a closed position; storing a wand assembly including a sanitizing head having an ultraviolet (UV) lamp in the storage chamber when not in use; and removing the wand assembly from the storage chamber to disinfect one or more components with UV light emitted by the UV lamp.

Portable sanitizing systems and methods

A portable sanitizing system, comprising a wand assembly including a sanitizing head having an ultraviolet (UV) lamp. A case assembly includes a cover coupled to a main body. The cover is configured to be moved between an open position that exposes a storage chamber and a closed position. The wand assembly is configured to be stored in the storage chamber when not in use and removed from the storage chamber to disinfect one or more components with UV light emitted by the UV lamp.

An example robotic device includes: a circumferential carriage configured to drive the robotic device along a rail configured to be mounted to a curved surface, the circumferential carriage comprising: (i) a frame base, (ii) a frame mounted to the frame base, (iii) one or more wheels coupled to the frame base and configured to engage with the rail, (iv) a worm gear arrangement, and (v) a main drive gear coupled to the worm gear arrangement and configured to engage with a rack disposed on the rail; and a transversal carriage comprising: (i) a cross slide slidably mounted to the frame, (ii) a transversal rack coupled to the cross slide, (iii) a cross slide motor mounted to the circumferential carriage, and (iv) a cross slide drive gear coupled to the cross slide motor and having gear teeth engaging with respective teeth of the transversal rack.

Flexible track system and robotic device for three-dimensional scanning of curved surfaces

An example cantilever assembly includes a cantilever including an anchor configured to be coupled to a support, a tip, and an arm positioned between the anchor and the tip, a hollow conductive tube positioned at the tip of the cantilever, and a magnet suspended inside the hollow conductive tube with a first spring and a second spring. The first spring and the second spring are positioned at a first end and a second end of the hollow conductive tube respectively, and the magnet is positioned between the first spring and the second spring. The magnet is configured to move coaxially inside the hollow conductive tube as permitted by the first spring and the second spring, and the magnet suspended inside the hollow conductive tube operates as a tuned mass damper (TMD) to limit a resonant response of the cantilever assembly.

Cantilever assemblies and methods of providing damping for cantilever assemblies

An aerodynamic body operable to both promote laminar flow and satisfy structural requirements is disclosed. A perforated panel skin comprises an inner surface and an outer surface of the aerodynamic body. A micro-lattice support structure is coupled to the inner surface and defines airflow gaps allowing suctioning of air from the outer surface through the perforated panel skin and into a plenum of the aerodynamic body. Rows of main beams of the micro-lattice support structure are aligned along land lines oriented in a substantially chord-wise direction relative to an airflow over the aerodynamic body.

Laminar flow panel

A structural assembly including a first member having an external side and an internal side, the first member defining a first member through-bore, a second member having an external side and an internal side, the second member defining a second member through-bore aligned with the first member through-bore, and a mechanical fastening system including a bushing at least partially received in the first member through-bore, the bushing defining a bushing through-bore and including a flange, wherein the flange is positioned in a gap between the internal side of the first member and the external side of the second member, a nut plate connected to the internal side of the second member, the nut plate defining a clearance bore aligned with the second member through-bore and the bushing through-bore, the nut plate including a nut, and a bolt extending through the bushing through-bore and into threaded engagement with the nut.

Fluid-tight mechanical fastening system and associated structural assembly

An aircraft includes a plurality of seats and an input device coupled to each of the plurality of seats. The aircraft also includes a remotely controlled nozzle positioned proximate each seat of the plurality of seats. Each nozzle includes an actuator assembly including at least one actuator and an actuator shaft. The at least one actuator is configured to move the actuator shaft between an open position and a closed position to control an airflow through the nozzle in response to a signal received from a respective input device of the input devices, wherein the signal represents a position of the actuator shaft.

Remote controlled air nozzles and methods of assembling the same

Systems, methods, and devices are configured to implement hydraulic actuators. Devices may include a housing having an internal surface defining an internal cavity that may have a substantially circular cross sectional curvature. The devices may include a rotor that includes a first slot having a substantially circular curvature. The devices may include a first vane disk partially disposed within the first slot of the rotor, where the first vane disk has a substantially circular external geometry. The first vane disk may be mechanically coupled to the rotor via the first slot, and the first vane disk may be configured to form a first seal with the internal surface of the housing. The devices may include a first separator device that may be configured to form a second seal with the internal surface of the housing and a third seal with an external surface of the rotor.

Systems, methods, and apparatus for rotary vane actuators

A wing includes a trailing edge, and a divergent trailing edge device slideable along an aft surface of the trailing edge between a stowed position and a fully deployed position. The trailing edge device is located entirely within the trailing edge when stowed, and it increases lift over drag of the wing when deployed.

Slidable divergent trailing edge device

A system for pneumatically actuating a split flap hingedly mounted near or at a trailing edge of an airfoil. The system includes a bladder system disposed between the split flap and the upper surface of the airfoil. The split flap is a small-chord (usually 1-3% of total wing chord) long-span lower panel which separates from the airfoil trailing edge by means of a hinge or a flexible lower skin. Deployment of the split flap is actuated pneumatically by the inflatable bladder system. The split flap may exist at a fixed wing trailing edge, a moving flap trailing edge, or an empennage trailing edge. The pneumatic bladder provides distributed force to extend and retract the split flap. This pneumatic approach eliminates extra drag, reduces cost and weight, and lessens flutter concerns.

Growing community of inventors

Bothell, WA, United States of America

Michael K Klein