Abstract: A composite assembly for an aircraft, the composite assembly including a first carbon fiber material structured for a portion of an outer skin surface of an aircraft, a second carbon fiber material stitched to the first carbon fiber material, wherein the second carbon fiber material is structured for a structural component of the aircraft, and wherein the stitching is configured to bind the first carbon fiber material and the second carbon fiber material, and wherein the aircraft further includes a single deck, wherein a cargo compartment and a passenger compartment are located on or above the single deck.

Abstract: Systems and methods are disclosed for generating subsurface property data as a function of position and time. Exemplary implementations may include obtaining a first initial subsurface property model and a first set of subsurface property parameters, obtaining training input data and a first training subsurface property dataset, generating a first conditioned subsurface property model, and storing the first conditioned subsurface property model.

Abstract: A composite assembly for a blended wing body aircraft, the composite assembly comprising: a first assembly comprising a first molded part, wherein the first molded part comprises a first plurality of fibers, the first molded part partially infused with a first resin, a second assembly oriented relative to the first assembly, the second assembly comprising a second molded part wherein the second molded part comprises a second plurality of fibers, the second molded part partially infused with a second resin, and a joining region, the joining region comprising at least a portion of first plurality of fibers and at least a portion of second plurality of fibers, the at least a portion of first plurality of fibers and the at least a portion of second plurality of fibers substantially adjacent and infused with a third resin.

Abstract: The present disclosure is directed to a blended wing body aircraft including a blended wing body, wherein the blended wing body is characterized by having no clear dividing line between wings and a main body along a leading edge of the aircraft; a cabin located within the main body and a transitional portion of the blended wing body; and a plurality of transmissive panels integrated into a ceiling of the cabin configured to transmit light from outside the blended wing body aircraft to inside the cabin.

Abstract: The present invention is directed to a cover window assembly comprising a multi-layer films of polymeric and inorganic materials for a variety of articles, and the related articles and methods. The cover window assembly exhibits high resistance to strain and impact damage for the articles including display devices, particularly flexible display devices.

Abstract: An aircraft with carbon fiber material comprising a blended wing body having a main body and wings with no clear demarcation between the wings and the main body along a leading edge of the aircraft, wherein the blended wing body comprises, at least an outer skin surface comprising a carbon fiber material, at least a structural element comprising the carbon fiber material, and at least a portion of the main body comprising the carbon fiber material and configured to contain a pressure vessel and at least a propulsor, the at least a propulsor attached to the blended wing body and configured to propel the aircraft.

Abstract: In a first aspect, a consolidated polymer film includes a first polymer layer having a first elastic modulus, wherein the first polymer layer comprises a non-melt-processible polymer comprising a polyimide, a poly(amide-imide), a block copolymer of a polyimide or a poly(amide-imide) or a mixture thereof, and a second polymer layer having a second elastic modulus, wherein the second polymer layer comprises a polyimide, a poly(amide-imide), a block copolymer of a polyimide or a poly(amide-imide) or a mixture thereof. A minor surface of the first polymer layer is in contact with a minor surface of the second polymer layer. The first elastic modulus is different from the second elastic modulus. The first and second polymer layers are bonded by consolidation.

Abstract: An apparatus for ingesting boundary layer flow on an aircraft, the apparatus includes a blended wing body, wherein the blended wing body is characterized by having no clear dividing line between wings and main body of the aircraft, wherein the blended wing body includes a nacelle located aft of a leading edge of the blended wing body, wherein the nacelle includes a propulsor configured to propel the aircraft, a primary duct, and a flow augmentation arrangement, wherein the flow augmentation arrangement is configured to accelerate a boundary layer flow in the airflow, wherein the flow augmentation arrangement further includes a secondary duct, wherein the secondary duct configured to ingest the boundary layer flow in the airflow from an inlet proximal to a forward portion of the nacelle to an outlet proximal to a rear portion of the nacelle and a tertiary duct between the primary duct and the secondary duct.

Abstract: an aircraft with high transport efficiency, wherein the aircraft include a blended wing body with a downward depressed upper aft surface, configured to operate at a high cruising level within a high cruise altitude range, wherein the blended wing body include a main body configured to accommodate a payload, and at least a wing, wherein the blended wing body include no striking demarcation between the main body and the at least a wing and at least a propulsor attached to the blended wing body and configured to propel the aircraft.

Abstract: The present disclosure is directed to a blended wing body aircraft including a blended wing body, wherein the blended wing body is characterized by having no clear dividing line between wings and a main body along a leading edge of the aircraft. The blended wing body aircraft also includes a plurality of transparent panels located in the top surface of the main body, wherein the plurality of transparent panels are located in channels, wherein the plurality of transparent panels allow the transmission of visible light.

Abstract: Described herein is a blended wing body aircraft. In some embodiments, a blended wing body aircraft may include a passenger cabin separated into two or more cabin bays. In some embodiments, two or more cabin bays may be separated by a structural element that runs through the passenger cabin along the longitudinal axis of the aircraft.

Abstract: A wearable device worn at a head region of a user includes electrodes for measuring a signal evoked by a visual stimulus. The electrodes include a first dry electrode configured to contact the skin around an car of the user. The se electrodes additionally include a second dry electrode configured to provide a reference signal for the measurement of the signal evoked by the visual stimulus.

Abstract: Aspects relate to aircraft and methods of use for aerodynamic control with winglet surfaces. In an aspect an exemplary aircraft includes a first wing having a first winglet at a distal end of the wing, wherein the first winglet comprises at least a first control surface at a first trailing edge of the first winglet and a second wing having a second winglet at a distal end of the wing, wherein the second winglet comprises at least a second control surface at a second trailing edge of the second winglet.

Abstract: Methods and systems for user communication in an online community and/or website are provided. User profile data may be accessed to from a memory. An analysis system compares the user profile data for the user with a time-dependent goal to determine a result. The time-dependent goal may be determined based on an analysis of a set of (successful) users. A user interface system generates a representation of the result for prompting the user to initiate a communication to a different user based on the time-dependent goal. The representation may comprise a metered representation indicating an amount of progress, by the user, toward the time-dependent goal.

Abstract: Technologies are described herein for a drag recovery scheme using a boundary layer bypass duct system. In some examples, boundary layer air is routed around the intake of one or more of the engines and reintroduced aft of the engine fan in the nozzle duct in a mixer-ejector scheme. Mixer-ejectors mix the boundary layer flow to increase mass flow.

Abstract: Described herein is a blended wing body aircraft. In some embodiments, a blended wing body aircraft may include a set of passenger loading doors on a first lateral side of the aircraft, and a set of passenger unloading doors on the second lateral side of the aircraft. In some embodiments, this configuration may allow for more efficient loading and unloading of blended wing body aircraft.

Abstract: Systems and methods for managing a power budget are provided. The method includes designating, by a power budget manager implemented on at least one processor, each of one or more applications with an individual quality of service (QoS) designation, the one or more applications executable by the at least one processor, assigning, by the power budget manager, a throttling priority to each of the one or more applications based on the individual QoS designations, determining, by the power budget manager, whether a platform mitigation threshold is exceeded, and responsive to determining that the platform mitigation threshold is exceeded, throttling, by the power budget manager, processing power allocated to at least one application of the one or more applications based on the throttling prioritization.

Abstract: The present disclosure is directed to a blended wing body aircraft including a blended wing body, wherein the blended wing body is characterized by having no clear dividing line between wings and a main body along a leading edge of the aircraft, at least a rib, wherein the at least a rib runs longitudinally from fore to aft of the main body, and a plurality of transparent panels located in the top surface of the main body, wherein the plurality of transparent panels are located in channels, wherein the channels are separated by the at least a rib.

Abstract: A water heater dip tube includes an elongated body having an inlet end and an outlet end. An inner volume is arranged within the elongated body. An anti-siphon orifice is arranged along the elongated body proximate the inlet end. The anti-siphon orifice extends through a wall of the elongated body. The dip tube further includes an elastomeric membrane secured to the elongated body. The elastomeric membrane is arranged in the vicinity of the anti-siphon orifice. The elastomeric membrane is operable to block fluid flow through the anti-siphon orifice when a pressure at the inlet end is greater than a pressure at the exterior of the dip tube adjacent to the anti-siphon orifice, and to allow fluid flow through the anti-siphon orifice when a pressure at the inlet end is less than a pressure at the exterior of the dip tube adjacent to the anti-siphon orifice.