Abstract: A hydro-thermal exchange unit (HTEU) for desalinating feed water in accordance with a humidification-dehumidification includes feed water, fresh water and gas conduit circuits for transporting feed water, fresh water, and gas, respectively. The unit also includes an evaporator through which a portion of the feed water conduit and the gas conduit pass. The evaporator causes evaporation of a portion of the feed water to produce vapor that is transported through the gas conduit. The unit also includes a condenser through which a portion of the gas conduit and the fresh water conduit pass. The condenser has input and output ports for coupling the gas and fresh water conduit circuits. The condenser extracts moisture from the vapor transported therethrough by the gas conduit. The extracted moisture is discharged through the fresh water conduit.

Abstract: An ice resistant structure is provided which includes a self-supporting, structural platform, a retaining, protective layer and a subsurface anti-icing (AI) and/or de-icing (DI) layer. The retaining, protective layer is disposed over the self-supporting, structural platform. The subsurface anti-icing (AI) and/or de-icing (DI) layer is located between the self-supporting, structural platform and the retaining, protective layer. The subsurface Al and/or DI layer is a functional layer such that an Al and/or DI agent is released to a surface of the retaining protective layer by an activation mechanism responsive to a change in an environmental condition.

Abstract: Embodiments of methods and apparatus for close formation flight are provided herein. In some embodiments, a method for establishing situational awareness during formation flight includes exchanging transponder signals between at least two aircraft, establishing two-way communication links between the at least two aircraft, exchanging telemetry data between the at least two aircraft, and assigning the roles of a leader and a follower to the aircraft.

Abstract: Embodiments of methods and apparatus for close formation flight are provided herein. In some embodiments, an apparatus for close formation flight, comprises a plurality of sensors for collecting measurements characterizing airflow near an aircraft. The plurality of sensors are attachable to at least one of a wing, fuselage, or tail of the aircraft, and the measurements provide information about airflow velocity in a direction transverse to a direction of the aircraft flight.

Abstract: Embodiments of the present invention provide an aircraft for vertical take-off and landing. In various embodiments, an aircraft assembly includes at least one first wing portion providing a lift force during a horizontal flight, at least one wing opening disposed on a vertical axis of the at least one first wing portion and at least one thruster positioned inside the at least one wing opening to provide vertical thrust during a vertical flight. The aircraft assembly can further include air vents positioned inside at least one of the wing openings. The air vents can further include louvres positioned over or under the air vents to open and close the wing openings. The thruster can further be used to provide flight control for the aircraft.

Abstract: Embodiments of methods and apparatus for close formation flight are provided herein. In some embodiments, a method of sensing three dimensional (3D) airflow by an aircraft includes: collecting measurements characterizing airflow near the aircraft; analyzing the collected measurements; creating, by a processor, a computer model predicting one or more 3D airflow patterns parameter values based on the analyzing; obtaining one or more additional measurements characterizing airflow near an aircraft of the plurality of aircraft, and evaluating an error between an airflow parameter value predicted by the computer model and the one or more additional measurement.

Abstract: Embodiments of methods and apparatus for close formation flight are provided herein. In some embodiments, a method of operating aircraft for flight in close formation includes establishing a communication link between a first aircraft and a second aircraft, assigning to at least one of the first aircraft or the second aircraft, via the communication link, initial positions relative to one another in the close formation, providing flight control input for aligning the first and second aircraft in their respective initial positions, tracking, by at least one aircraft in the close formation, at least one vortex-generated by at least one other aircraft in the close formation, and based on the tracking, providing flight control input to adjust a relative position between the first aircraft and the second aircraft.

Abstract: Embodiments of air flow sensing systems are provided herein. In some embodiments, one or more sensors are positionable on an aircraft and dimensioned and arranged to measure vector components of airflow velocity having at least one of a transverse or streamwise direction relative to a flight direction of the aircraft. In some embodiments, the one or more sensors are positioned in front of an aircraft wing and distributed as an array of sensors along the span of the aircraft wing.

Abstract: An aircraft for vertical take-off and landing includes an aircraft assembly which includes at least one first wing portion providing a lift force during a horizontal flight, at least one wing opening disposed on a vertical axis of the at least one first wing portion and at least one propeller-based thruster positioned inside the at least one wing opening to provide vertical thrust during a vertical flight. The aircraft assembly can further include air vents positioned inside at least one of the wing openings. The air vents can further include louvres positioned over or under the air vents to open and close the wing openings. The thruster can further be used to provide flight control for the aircraft.

Abstract: A method is provided for fabricating a thin-film semiconductor device. The method includes providing a plurality of raw semiconductor materials. The raw semiconductor materials undergo a pre-reacting process to form a homogeneous compound semiconductor material. This pre-reaction typically includes processing above the liquidus temperature of the compound semiconductor. The compound semiconductor material is reduced to a particulate form and deposited onto a substrate to form a thin-film having a composition and atomic structure substantially the same as a composition and atomic structure of the compound semiconductor material.

Abstract: Embodiments of the present invention provide an alternative distributed airborne transportation system. In some embodiments, a method for distributed airborne transportation includes: providing an airborne vehicle with a wing and a wing span, having capacity to carry one or more of passengers or cargo; landing of the airborne vehicle near one or more of passengers or cargo and loading at least one of passengers or cargo; taking-off and determining a flight direction for the airborne vehicle; locating at least one other airborne vehicle, which has substantially the same flight direction; and joining at least one other airborne vehicle in flight formation and forming a fleet, in which airborne vehicles fly with the same speed and direction and in which adjacent airborne vehicles are separated by distance of less than 100 wing spans.

Abstract: Embodiments of methods for providing distributed airborne wireless communications are provided herein. In some embodiments, a method of providing wireless communication services includes: receiving a radio frequency (RF) signal from a first area by a distributed airborne communication payload, wherein the distributed airborne communication payload is comprised of sections located on respective ones of a plurality of airborne platforms; relaying the RF signal along the sections located on different airborne platforms; and transmitting the RF signal to a second area.

Abstract: A multi-functional, multi-layer film or skin which may be used as a covering for a structure or platform incorporates an integrated photovoltaic element and an integrated RF antenna element. The film or skin is suitable for use in various applications, including those involving autonomous, self-powered, mobile communication systems and especially for use as a skin or covering for solar powered aircraft and UAVs. Planar PV cells and planar RF antenna are used to facilitate their integration into the film or skin. The PV cells and RF antenna are configured to face operate outward from opposite faces of the skin. The film or skin addresses potential problems arising from conflicting directional requirements for PV orientation and antenna pointing on mobile platforms. This is accomplished by employing wide angle AR coatings on the PV elements and electrical controls to steer the RF antenna.

Abstract: Embodiments of the present invention provide an alternative distributed airborne transportation system. In some embodiments, a method for distributed airborne transportation includes: providing an airborne vehicle with a wing and a wing span, having capacity to carry one or more of passengers or cargo; landing of the airborne vehicle near one or more of passengers or cargo and loading at least one of passengers or cargo; taking-off and determining a flight direction for the airborne vehicle; locating at least one other airborne vehicle, which has substantially the same flight direction; and joining at least one other airborne vehicle in flight formation and forming a fleet, in which airborne vehicles fly with the same speed and direction and in which adjacent airborne vehicles are separated by distance of less than 100 wing spans.

Abstract: Embodiments of the present invention provide an aircraft for vertical take-off and landing. In various embodiments, an aircraft assembly includes at least one first wing portion providing a lift force during a horizontal flight, at least one wing opening disposed on a vertical axis of the at least one first wing portion and at least one thruster positioned inside the at least one wing opening to provide vertical thrust during a vertical flight. The aircraft assembly can further include air vents positioned inside at least one of the wing openings. The air vents can further include louvres positioned over or under the air vents to open and close the wing openings. The thruster can further be used to provide flight control for the aircraft.

Abstract: Embodiments of the present invention provide an alternative distributed airborne transportation system. In some embodiments, a method for distributed airborne transportation includes: providing an airborne vehicle with a wing and a wing span, having capacity to carry one or more of passengers or cargo; landing of the airborne vehicle near one or more of passengers or cargo and loading at least one of passengers or cargo; taking-off and determining a flight direction for the airborne vehicle; locating at least one other airborne vehicle, which has substantially the same flight direction; and joining at least one other airborne vehicle in flight formation and forming a fleet, in which airborne vehicles fly with the same speed and direction and in which adjacent airborne vehicles are separated by distance of less than 100 wing spans.

Abstract: Methods and apparatus for supplying power to an electrical line or grid by using high-frequency alternating current (HFAC) are provided herein. In some embodiments, an apparatus for collecting and transmitting electrical power to an AC line operating at a line frequency may include a plurality of high frequency AC power sources; a high frequency AC bus, connected to each of the high frequency AC sources; and a line frequency converter, the input of which is connected to the high frequency AC bus and the output of which is connectable to the AC line.

Abstract: A multi-input electrical power conversion device is provided for converting multiple DC energies each arising from different junctions in a multi-junction solar cells into AC energy. The device includes a plurality of electrical inputs for receiving the multiple DC energies from at least one multi junction solar cell. The number of DC energies id no less than the number of junctions in the multi-junction solar cell. The device also includes at least one DC-to-AC circuit for receiving the multiple DC energies from the plurality of electrical inputs and at least one electrical output receiving at least one AC energy from the DC to AC circuit. The device also includes at least one MPPT circuit operatively coupled to the DC to AC circuit.

Abstract: A multilayer film or skin for free space optical data transmission includes a first outer layer. The first outer layer has a first laterally extending area that transmits optical data signals received over a range of incident angle. A second layer that includes a second laterally extending area underlies the first layer. At least a portion of the optical data signals received by the second layer from the first outer layer is focused or otherwise concentrated into a substantially reduced area. An optical detector receives the concentrated optical data signals from the second layer. An electrical connection extends from the optical detector to an external receiving device. The multilayer film or skin may be used, for example, in applications involving mobile free space optical communication platforms where low profile, volume and mass and/or enhanced platforms are important.

Abstract: Embodiments of methods and apparatus for providing distributed airborne wireless communications are provided herein. In some embodiments, an airborne wireless service area includes: an airborne fleet, comprised of a plurality of aircraft, wherein the airborne fleet is configured to transmit a plurality of first beams at a first radio frequency (RF), wherein the plurality of first beams are characterized by corresponding first frequency band, channel, bandwidth, transmission format, uneven angular field intensity distribution, and boundaries, wherein neighboring first beams have an overlap region, and wherein at least one of the following characteristics is different between the neighboring first beams: frequency band, channel, or transmission format; and a plurality of first communication cells defined by respective boundaries of the plurality of first beams, wherein each of the first communication cells are characterized by their size, shape, and position.