The Boeing Company

Sina Sam Golshany

Todd William Erickson

Adriana Willempje Blom

Christopher R Holtorf

Derek R Alderks

Junghyun Ahn

Jacqueline A Artis

Shelly A Songstad

Natalie Daughtry

Paul Robert Tretow

Matthew W Orr

Gnanulan Canagaratna

David Miles Huntly

Lowell Bruce Campbell

Andrew Walter Fassmann

Martin M Withington

David A Rathke

Daniel Wajerski

Tarek H Elghoroury

David M Huntly

An artillery shell is fired out of a gun towards a fire. A trigger releases a fire-retarding material from the artillery shell to retard the fire.

Fire-retarding artillery shell

A system includes a signal generator that is configured to generate a first electrical signal. The system also includes a light source configured to generate a light beam based on the first electrical signal. The light source is also configured to direct the light beam towards a structural member of an aircraft. The system also includes a photoelectric sensor configured to receive a reflected light beam and convert the reflected light beam to a second electrical signal. The reflected light beam corresponds to a portion of the light beam that is reflected from one or more optical reflectors coupled to the structural member. The system also includes circuitry configured to estimate a location of a center-of-gravity of the aircraft based on a timing difference between the first electrical signal and the second electrical signal.

Optical device for estimating a center of gravity of an aircraft

In a particular implementation, a method includes generating an initial weight estimate associated with an aircraft based on a reference operational empty weight (OEW) and at least one of a latitude or an altitude of the aircraft at a first location. The reference OEW is predetermined at a second location that is distinct from the first location. The method includes determining an additional load capability of the aircraft based on a difference between the initial weight estimate and the reference OEW. The method further includes generating an output that indicates the additional load capability.

System and method for determining a load capability

A propulsion unit having reduced noise employs a rotor having a plurality of variable pitch blades. A tensioning joint mechanism is carried within each blade and a tension element is engaged by the tension joint mechanism. The tension element is configured to maintain tension between the blades in the rotor and the tensioning joint mechanism adapted to allow variation of pitch of the blades without altering tension in the tension element.

Laterally reinforced variable pitch rotor

A system and method determine a size and a shape for identical geodesic modules that are used to form a structure. The system and method may include analyzing input data regarding a size and a shape of the structure to be formed, and determining the size and the shape for each of the identical geodesic modules based on the size and the shape of the structure to be formed. The structure may include a framework including the identical geodesic modules. Each of the geodesic modules has a size and a shape that are the same as all of the other of the geodesic modules. A forming system and method position a framework and a covering skin of the structure in relation to a mandrel, and drill and rivet the framework to the covering skin with a plurality of operating heads.

Systems and methods for determining sizes and shapes of geodesic modules

Systems and methods for manufacturing a tubular structure

A propulsion system for a transport aircraft employs a gas turbine core coupled to a wing. A ducted fan is coupled to the core gas turbine extending downstream from and integrated in a trailing edge of the airplane wing.

Integrated pusher turbofan for aircraft

In one aspect a propulsion system comprises an engine and a drive assembly coupled to the engine, comprising a first driveshaft rotatable in a first direction about a first axis, a first fan coupled to the first driveshaft to rotate in the first direction, and a clutch assembly to selectively disengage the first fan from the first driveshaft. Other aspects may be described.

Contra-rotating open fan propulsion system

Systems and methods provide for the mitigation of vibrational forces acting on a horizontal stabilizer of an aircraft. According to one aspect, a damper is coupled to a front portion of a horizontal stabilizer to dampen vibrations in a first degree of freedom, with another damper coupled to a mounting point of the horizontal stabilizer to dampen vibrations in a second degree of freedom. The dampers may be passive, operating independently to mitigate vibrational forces, or active, applying a mitigating force to the horizontal stabilizer based on real-time or estimated vibration states.

Growing community of inventors

Lynwood, WA, United States of America

Sina Sam Golshany