The Boeing Company

Aaron Jonathan Kutzmann

Kevin Reed Lutke

Richard P Ouellette

Max Urban Kismarton

Robert Erik Grip

John Charles Vassberg

David J Manley

Neal A Harrison

Robert D Gregg, Iii

Blaine Knight Rawdon

Frederic Lacaux

Darold B Cummings

David A Deamer

Edward L Lawson

Nathaniel J Noel

James M Ball

Kamiar J Karimi

Eugene V Solodovnik

Sergey D Barmichev

Christopher K Droney

Zachary Charles Hoisington

John Anthony Trela

Mary Eileen Beckman

Justin G Albright

Douglas E Ferguson

Antonio B Gonzales

Esther S Zidovetzki

Patrick R Darmstadt

Alejandro Silva

Steven Edmon Chapel

William Noll Kamerow

Stephen D Griffin

Robb Gregg, Iii

Steve Hollowell

Nicholas J Silveri

There is provided a segmented vacuum jacketed tank system. The system includes a segmented structurally integrated vacuum tank having a vacuum tank main portion between vacuum tank end portions. The vacuum tank main portion includes a vacuum tank skin having an outer surface and an inner surface, vacuum tank skin segments, and a longitudinal cross section with a profile geometry configured for buckling prevention for the vacuum tank skin under external pressure loads. The vacuum tank main portion includes multipurpose stiffener member(s) configured to carry one or more of system transport line(s), a liquid fuel, or a nitrogen gas in an interior. The system includes a pressure tank within the segmented structurally integrated vacuum tank. The pressure tank is configured to store a cryogenic fluid and includes a pressure tank main portion between pressure tank end portions. The system further includes a vacuum cavity.

Segmented vacuum jacketed tank system and method of using the same

A tank system includes a vacuum tank having a vacuum tank skin, and a pressure tank mounted within the vacuum tank having one or more pressure tank skin segments having a total circumference that is less than that of a complete circle, resulting in one or more longitudinal gaps respectively between the one or more pressure tank skin segments. The tank system includes one or more gap control mechanisms configured to control a width of the one or more longitudinal gaps in a manner facilitating movement of the one or more pressure tank skin segments between at least the following positions: a retracted position in which there is a radial gap between each pressure tank skin segment and the vacuum tank skin, and a fully extended position in which at least a portion of each pressure tank skin segments is in contact with the vacuum tank skin.

System and method of controlling the circumference of a pressure tank mounted within a vacuum tank

There is provided a structurally integrated vacuum tank that includes a vacuum tank main portion extending between vacuum tank end portions. The vacuum tank main portion includes a vacuum tank skin forming a cylinder. The vacuum tank skin has a longitudinal cross section with a profile geometry configured for buckling prevention for the vacuum tank skin under external pressure loads. The vacuum tank skin is configured to provide a pressure barrier between an outside ambient pressure and a vacuum in an interior of the vacuum tank main portion. The vacuum tank main portion further includes a plurality of stiffener members coupled to surface portions of the vacuum tank skin. The vacuum tank skin and the plurality of stiffener members are configured to carry structural loads.

Structurally integrated vacuum tank and method of using the same

A lift system for an aircraft includes a first galley cart, a second galley cart, a floor deck, and a frame. The frame defines a first storage zone, a second storage zone, and a third storage zone that are stacked. A bottom end of the first storage zone is aligned with the floor deck, a top end of the second storage zone is aligned with the floor deck, and a bottom end of the third storage zone is aligned with a top end of the first storage zone. The lift system also includes a first lift configured to move the first galley cart from the first storage zone to the second storage zone and a second lift configured to move the second galley cart from the first storage zone to the third storage zone.

Lift system for aircraft

There is provided a tank system having a removable plug assembly. The tank system has a vacuum tank with a vacuum tank main portion, a pressure tank mounted within the vacuum tank, and a vacuum cavity formed between the pressure tank and the vacuum tank. The pressure tank has the removable plug assembly with removable plug element(s), each configured to plug and to unplug opening(s) in the pressure tank, and a retraction mechanism within the pressure tank coupled to the removable plug element(s). When an emergency condition occurs, the retraction mechanism is activated to pull the removable plug element(s) away from the opening(s) and into the interior of the pressure tank, to allow a cryogenic fluid to exit from the pressure tank, through the opening(s), and into the vacuum cavity, and when the vacuum tank has a breach, to allow the cryogenic fluid to further exit out into air.

Tank system having removable plug assembly and method of using the same

Systems for suppressing adverse exothermic reactions in an energy storage container. One energy storage system includes a container configured to support a plurality of battery cells; a plurality of battery cells disposed inside and supported by the container; an agent supply port attached to the container; and a tube disposed inside the container and having a closed end and an open end. The open end of the tube is in fluid communication with the agent supply port. The tube comprises fusible portions which are designed to melt or soften at a temperature which is lower than the melting or softening temperature of another portion of the tube. In response to melting or softening of the fusible portions of the tube, pressurized exothermic reaction-suppressing agent is distributed inside the container via the tube.

Systems for suppressing adverse exothermic reactions in energy storage containers

An electric propulsion unit comprising a housing, an AC motor, a beta rod, a propeller, a governor, an inverter, and a controller. The AC motor is disposed within the housing and includes bearings supported inside the housing, a hollow motor shaft rotatably coupled to the housing by the bearings, a stator which is supported by the housing, and a rotor which is mounted to the hollow motor shaft. The beta rod is axially translatable inside the hollow motor shaft. The propeller is mechanically coupled to the hollow motor shaft. The propeller includes propeller blades having an adjustable pitch angle which depends on an axial position of the beta rod. The governor is configured to adjust a pitch angle of the propeller blades by actuating axial translation of the beta rod. The controller is disposed inside the housing and configured to control the pitch angle of the propeller blades.

Integrated electric propulsion unit

Certain aspects of the present disclosure provide an ice management system, including: a plurality of pulsejets located within an interior volume of an aircraft and configured to heat an aircraft surface, wherein each pulsejet of the plurality of pulsejets comprises: an inlet; a combustor; a fuel source; and an exhaust nozzle; and a plurality of intake apertures in the aircraft, wherein each intake aperture of the plurality of intake apertures corresponds to an inlet of one pulsejet of the plurality of pulsejets.

Anti-ice pulsed jet hiller reactor

A solar powered aircraft including a modular main wing and a pair of relatively large modular winglets attached to the transverse end portions of the main wing. To collect solar radiation, including relatively low-angle radiation, solar panels are mounted to both the main wing and the winglets. In some embodiments, the aspect ratio of the main wing is relatively low, such as between 9 and 15, i.e., the main wing is relatively deep compared to its wing span. In some embodiments, the winglets are relatively long, such as in the range of 0.2 to 0.7 times the length of the main wing semi-span. In some embodiments, a truss-like spar passes through and helps support the wing and the winglets.

Solar powered airplane

A light-weight stiffened wing airfoil includes at least one wing segment (). The wing segment comprises an upper () and a lower skin assembly (), wherein each of the upper and lower skin assemblies incorporates a plurality of inwardly facing stringers (); a first rib (-) at a distal end of the wing segment and a second rib (-) at a proximal end of the wing segment; a plurality of rib trusses () extending from the first and second ribs to the opposing skin assembly (); and a plurality of support members extending from the inwardly facing stringers to the opposing skin assembly.

Wing airfoil stiffening for solar powered aircraft

A method and apparatus for operating an airfoil system. A gas may be generated. The gas may be sent into an inflatable airfoil system comprising an inflatable air foil and a section. The inflatable airfoil may have an inner end and an outer end in which the inflatable airfoil may be comprised of a number of materials that substantially pass electromagnetic waves through the inflatable airfoil. The section may have a number of openings in which the inner end of the inflatable airfoil may be associated with the section. The section may be configured to be associated with a fuselage. The number of openings may be configured to provide communications with an interior of the inflatable airfoil. The section with the number of openings may be configured to reduce reflection of the electromagnetic waves encountering the section.

Inflatable airfoil system configured to reduce reflection of electromagnetic waves

A rocket comprises at least one propulsion unit including a pivotable rocket motor, a spring-assisted one-time deployment mechanism, and a release mechanism. The pivotable rocket motor is pivotable between a stowed position and a deployed position. The spring-assisted one-time deployment mechanism moves the rocket motor from the stowed position to the deployed position when the deployment mechanism is released by the release mechanism. Outer geometry of the rocket is changed as the rocket motor is moved to the deployed position.

Spring-assisted deployment of a pivotable rocket motor

Inflatable airfoil system having reduced radar observability

A multiple stage orbital delivery vehicle that uses tractor propulsion to launch the vehicle into space. Only the upper stage of the vehicle includes an engine and avionics allowing the lower stages to be only liquid propellant tanks that may be dumped when empty. The liquid propellant may be either monopropellant or bi-propellant. The upper stage may include multiple nozzles that burn the propellant. Alternatively, the upper stage may include an aerospike engine instead of nozzles. The multiple stage orbital delivery vehicle may be air launched from an airborne aircraft or may be launched from the ground.

Multiple stage tractor propulsion vehicle

Embodiments provide a flying boom that is capable of refueling both receptacle-equipped aircraft and probe-equipped aircraft. In one embodiment, a flying boom includes a refueling tube at an end of the flying boom that is adapted to extend from the end of the flying boom to refuel receptacle-equipped aircraft. The flying boom further includes a retractable hose and drogue assembly at the end of the flying boom that is adapted to extend from the end of the flying boom to refuel probe-equipped aircraft.

Growing community of inventors

Long Beach, CA, United States of America

Aaron Jonathan Kutzmann