The Boeing Company

Jetzero, Inc.

United States of America As Represented by the Administrator of Nasa

John Charles Vassberg

Dino L Roman

Mark DeHaan

Robert Erik Grip

Neal A Harrison

Blaine Knight Rawdon

Adam P Malachowski

Christopher A Vegter

Douglas M Friedman

Robert D Gregg, Iii

Aaron Jonathan Kutzmann

David J Manley

Max Urban Kismarton

John Joseph Brown

Christopher K Droney

Ted K Rothaupt

David T Yeh

Robert D Gregg

Mark Allan Page

Alan Zachary Ullman

Kevin Reed Lutke

James Douglas McLean

Anthony J Sclafani

Arthur Gregory Powell

Edward L Lawson

Lie-Mine Gea

Nathaniel J Noel

Antonio B Gonzales

Charles Daniel Peyton

Michael W Traffenstedt

Richard L Campbell

Raphael Diaz

David P Witkowski

James D McLean, Jr

Robb Gregg, Iii

Steve Hollowell

Tony J Sclafani

Steven E Krist

David M Pitera

Mark Dehaan

Mark A Dehaan

In another aspect, a method for fueling an aircraft, the method including storing liquified gas fuel using a fuel tank, wherein the fuel tank is configured to store liquified gas fuel, fueling an aircraft using a fuel line. Fueling the aircraft may additionally include the fuel tank with liquified gas fuel to a desired level, wherein a desired level comprises fuel for a plurality of flights plus reserves. Filling may also include removing the fuel line as a function of the desired level. The method may additionally include venting the fuel tank using a vent line in fluid connection to the fuel tank. The fuel tank may then be prepared for flight as a function of a desired level. Finally, the method includes flying a plurality of flights using the aircraft.

Method for fueling an aircraft

There is provided an expandable strut assembly for a wing of an aircraft, having a strut with a strut cross section with an airfoil shape, and the strut having an outboard end coupled to the wing, an inboard end coupled to a fuselage, and an elongate body, and having at least one shape transition assembly connected to the strut. Each shape transition assembly is configured to transition the strut between a contracted position and an expanded position, and is configured to transition the strut cross section between a contracted airfoil shape and an expanded airfoil shape. Each shape transition assembly has a shape transition mechanism attached to an interior of the strut. The shape transition mechanism includes fixed length structural members, and a drive mechanism of variable length structural member(s), includes an actuation mechanism connected to the shape transition mechanism, and an activation mechanism coupled to the actuation mechanism.

Expandable strut assembly for a wing of an aircraft and method of using the same

An aircraft with an engine support structure, the aircraft including at least an engine wherein the at least engine is top mounted to an aircraft, a main body, and an engine support structure including a plurality of hoop structures, wherein at least one horseshoe structure is located forward of the center of gravity to the at least engine.

Aircraft with an engine support structure

A freighter aircraft for long-distance travel, the freighter aircraft comprising a blended wing body having a main body, a transition, and wings with no clear demarcation between the wings and the main body along a leading edge of the freighter aircraft, at least a propulsor, the at least a propulsor attached to a portion of the main body and configured to propel the freighter aircraft through air, a fuel storage located within the blended wing body, the fuel storage having a fuel capacity wherein the fuel capacity is configured for long-range flight, and a cargo bay located within the main body; the cargo bay configured to have a freighter capacity, wherein freighter aircraft is a long-range aircraft, the freighter aircraft including a ton-miles per sortie between 135,000 and 450,000.

Long range freighter aircraft

Subsonic turbofan engines with variable outer guide vanes (OGVs) and associated methods. A subsonic turbofan engine includes an engine core configured to generate a torque, a fan configured to accelerate an air flow, an engine nacelle, and a plurality of OGVs positioned downstream of the fan. Each OGV is configured to transition among a plurality of OGV configurations defined between and including a nominal configuration and a reduced-drag configuration. The subsonic turbofan engine is configured to operate only at subsonic speeds. In examples, methods of operating a subsonic turbofan engine include transitioning each of a plurality of OGVs from a nominal configuration to a reduced-drag configuration. Transitioning each OGV from the nominal configuration to the reduced-drag configuration is performed while the subsonic engine operates at subsonic speeds.

Subsonic turbofan engines with variable outer guide vanes and associated methods

There is provided a vacuum volume reduction system having a volume reduction assembly of a fluid fill assembly coupled to a station wall of a vacuum tube vehicle station, to reduce a volume, under vacuum, in the vacuum tube vehicle station, when a vacuum transport tube vehicle is positioned in the volume at the vacuum tube vehicle station. The fluid fill assembly includes one or more containers, each containing a fluid, and fluid transport member(s), to transport the fluid from the container(s) to one or more enclosed volume portions formed between an exterior of the vacuum transport tube vehicle and an interior of the station wall. The fluid fill assembly further includes one or more fluid pump assemblies attached to the fluid transport member(s), and a control and power system. The vacuum volume reduction system further includes recessed area(s), a vent-to-vacuum assembly coupled to the recessed area(s), and seal elements.

Vacuum volume reduction system and method with fluid fill assembly for a vacuum tube vehicle station

A vacuum transport tube vehicle for evacuating a vacuum transport tube has a first end, a second end, and a body comprising a piston head. The vehicle has a blade-actuator assembly, comprising a circumferential blade member sealed to the piston head and having a blade perimeter portion defining a first end outer surface forming an annular gap with an inner surface of the vacuum transport tube. The vehicle further includes a plurality of blade segment actuators arranged circumferentially around the piston perimeter portion and configured to actively adjust a radial position of the blade member at the corresponding blade circumferential locations in a manner accommodating non-uniformities in an inner surface profile of the vacuum transport tube, and maintaining the annular gap at a substantially constant and relatively short gap distance during movement of the vehicle through the vacuum transport tube.

Vacuum transport tube vehicle, system, and method for evacuating a vacuum transport tube

An ultrashort nacelle configuration employs a fan cowl having an exit plane and a serrated trailing edge. A variable pitch fan is housed within the fan cowl. The variable pitch fan has a reverse thrust position inducing a reverse flow through the exit plane and into the fan cowl. The serrated trailing edge forms a plurality of vortex generators configured to induce vortices in the reverse flow.

Fan cowl with a serrated trailing edge providing attached flow in reverse thrust mode

Split winglet

There is provided a turbofan engine for an aircraft. The turbofan engine has a core with a fan cowl and a variable pitch fan (VPF) configured to only rotate in a first rotation direction. The VPF has a plurality of fan blades each configured to over-pitch to an over-pitch position relative to a feathered position. The turbofan engine has outer guide vanes (OGVs) axially disposed downstream of the VPF, and has a rotation control device to prevent the VPF from rotating in a second rotation direction opposite the first rotation direction, during an engine out (EO) condition of the turbofan engine. When the VPF is prevented from rotating during the EO condition, the fan blades are over-pitched to the over-pitch position relative to the feathered position, to achieve no or minimal air flow separation about the OGVs, and to reduce drag of the turbofan engine during the EO condition.

Aircraft turbofan engine having variable pitch fan and method of over-pitching the variable pitch fan in an engine out condition to reduce drag

There is provided a propulsion system for an aircraft, the system having a low-fan-pressure-ratio engine configured to be mounted, in a forward over-wing-flow installation, to a wing of the aircraft. The engine has a core, a variable pitch fan, and a nacelle having a nacelle trailing edge with a top-most portion positioned above a wing leading edge. The engine has an L/D ratio of the nacelle in a range of from 0.6 to 1.0, and a fan-pressure-ratio in a range of from 1.10 to 1.30. The forward over-wing-flow installation enables, during all flight phases of the aircraft, a fan flow exhaust to flow behind the nacelle, and to be bifurcated by the wing leading edge, so the fan flow exhaust flows both over the wing and under the wing. During a cruise flight phase of the aircraft, the engine minimizes scrubbing drag of the fan flow exhaust to the wing.

Aircraft propulsion system with a low-fan-pressure-ratio engine in a forward over-wing flow installation, and method of installing the same

A modular tube volume reduction assembly for use at a vacuum tube vehicle station is provided. The assembly includes a modular station vacuum tube having a tube volume and a plurality of cavities longitudinally formed around a circumference of the modular station vacuum tube, and a volume reduction assembly integrated with the modular station vacuum tube, where the volume reduction assembly includes a plurality of blocks longitudinally coupled to a cavity interior of each of the plurality of cavities. The assembly includes a control system coupled between the modular station vacuum tube and the blocks. The control system radially moves the blocks to and from a vehicle outer surface of a vacuum transport tube vehicle at the vacuum tube vehicle station. The assembly displaces the tube volume between a station wall and the vehicle outer surface, and reduces the volume to be evacuated at the vacuum tube vehicle station.

Vacuum volume reduction system for a vacuum tube vehicle station

A vacuum transport tube vehicle, system, and method for evacuating a vacuum transport tube are provided. The vehicle has a first end having a first end outer surface. An annular gap is formed between the first end outer surface and an inner surface of the vacuum transport tube. The vehicle has a second end having a second end outer diameter, and a body in the form of a piston with a structural framework. The vehicle has an orifice extending from a first inlet portion in the first end to a second outlet portion of the vehicle. The vehicle has a drive assembly coupled to the body, and a power system. The vehicle evacuates the vacuum transport tube by reducing pressure within the tube with each successive vehicle pass through the tube, until a desired pressure is obtained and a vacuum is created in the interior of the tube.

A vacuum volume reduction system and method for reducing a volume to be evacuated at a vacuum tube vehicle station are provided. The system has a station vacuum tube in an interior of a station wall of the vacuum tube vehicle station. The station vacuum tube has a tube volume. The system has a volume reduction assembly coupled to the station vacuum tube, and a control system for radially moving the assembly to and from a vehicle outer surface of a vacuum transport tube vehicle, to engage around the vehicle outer surface, for loading and unloading of passengers and/or cargo. The system further has door seal(s), an air supply assembly, and a vent-to-vacuum assembly. The system displaces the tube volume between the station wall and the vehicle outer surface, and in turn, reduces a volume to be evacuated at the vacuum tube vehicle station.

Vacuum volume reduction system and method for a vacuum tube vehicle station

A winglet system for an aircraft wing includes an upper winglet and a lower winglet mounted to a wing. The lower winglet has a static position when the wing is subject to an on-ground static loading. The lower winglet is configured such that upward deflection of the wing under an approximate 1-g flight loading causes the lower winglet to move upwardly and outwardly from the static position to an in-flight position resulting in an effective span increase of the wing under the approximate 1-g flight loading relative to the span of the wing under the on-ground static loading. The lower winglet is configured to aeroelastically deflect upwardly under the approximate 1-g flight loading and further increase the effective span of the wing beyond the effective span increase that is caused by the upward deflection of the wing.

Split winglet system

Growing community of inventors

Long Beach, CA, United States of America

John Charles Vassberg