Redox flow devices are described including a positive electrode current collector, a negative electrode current collector, and an ion-permeable membrane separating said positive and negative current collectors, positioned and arranged to define a positive electroactive zone and a negative electroactive zone; wherein at least one of said positive and negative electroactive zone comprises a flowable semi-solid composition comprising ion storage compound particles capable of taking up or releasing said ions during operation of the cell, and wherein the ion storage compound particles have a polydisperse size distribution in which the finest particles present in at least 5 vol % of the total volume, is at least a factor of 5 smaller than the largest particles present in at least 5 vol % of the total volume.

High energy density redox flow device

A system and method for power management is described that provides for monitoring and controlling a regenerative fuel cell and at least one powered device. The power management system includes a communication interface to facilitate data transmission, a communication device for monitoring and controlling a regenerative fuel cell and at least one powered device, the communication device providing for sending data to and receiving data from at least one powered device over a communication interface, a regenerative fuel cell for providing storage and supply of electricity, and a power interface for allowing electricity generated by the regenerative fuel cell to power at least one powered device.

System and method for power management

A hover aircraft employs an air impeller engine having an air channel duct and a rotor with outer ends of its blades fixed to an annular impeller disk that is driven by magnetic induction elements arrayed in the air channel duct. The air-impeller engine is arranged vertically in the aircraft frame to provide vertical thrust for vertical takeoff and landing. Preferably, the air-impeller engine employs dual, coaxial, contra-rotating rotors for increased thrust and gyroscopic stability. An air vane assembly directs a portion of the air thrust output at a desired angle to provide a horizontal thrust component for flight maneuvering or translation movement. The aircraft can employ a single engine in an annular fuselage, two engines on a longitudinal fuselage chassis, three engines in a triangular arrangement for forward flight stability, or other multiple engine arrangements in a symmetric, balanced configuration. Other flight control mechanisms may be employed, including side winglets, an overhead wing, and/or air rudders or flaps. An integrated flight control system can be used to operate the various flight control mechanisms. Electric power is supplied to the magnetic induction drives by high-capacity lightweight batteries or fuel cells. The hover aircraft is especially well suited for applications requiring VTOL deployment, hover operation for quiet surveillance, maneuvering in close air spaces, and long duration flights for continuous surveillance of ground targets and important facilities requiring constant monitoring.

Aerodynamically stable, VTOL aircraft

In one embodiment, an apparatus includes a first member that supports a magnetic flux carrying member and a second member that supports a magnetic flux generating member disposed for movement relative to the first member. An air gap control system is coupled to at least one of the first member or the second member and includes an air gap control device that is separate from a primary magnetic flux circuit formed between the first member and the second member. The air gap control device is configured to exert a force on one of the first and second members in response to movement of the other of the first and second members in a direction that reduces a distance between the first and second members to maintain a minimum distance between the first and second members and/or substantially center the one of the first and second members within the other.

Air gap control systems and methods

A refuelable electrochemical power source includes one or more electrochemical cells adapted to employ particulate material electrodes. The one or more cells include a cell body defining an interior cell cavity, a flow path in the cell cavity through which particulate material and fluid flow, an electroactive zone within the cell cavity, and a fluid mechanic device adjacent or within the flow path capable of filling the electroactive zone or maintaining the electroactive zone in a constantly full or maximum electroactivity condition. A method for filling or maintaining one or more cells of a refuelable electrochemical power source at a constantly full condition includes providing the above-described apparatus and constantly, periodically, or intermittently circulating particulate material and fluid through the flow path in the one or more cells, past the fluid mechanic device, so that the electroactive zone of the one or more electrochemical cells is maintained in a constantly full or maximum electroactivity condition.

Refuelable electrochemical power source capable of being maintained in a substantially constant full condition and method of using the same

An aircraft ( 10 ) is disclosed that comprises a fuselage ( 12 ) with first and second wings ( 14 ) non-rotatably secured to and extending from sides of the fuselage ( 12 ). Inner and outer tracks are secured to and encircle the fuselage ( 12 ), and airfoils ( 20 ) are operably secured between the inner and outer tracks. Means are provided for rotating the airfoils ( 20 ). The means for rotating the airfoils may be comprised of first and second drive coils ( 40 ), and first and second alternators ( 80 ) may be operably coupled to the first and second drive coils ( 40 ), respectively, to provide redundant power supplies. Permanent magnets ( 44 ) in the rotor hub may be arranged in a Halbach array or may be arranged to provide a series of alternating, opposite magnetic poles. Separate drive and suspension coils ( 38 ) may be provided in the stator ( 16 ). The concept may find further application in a lift fan or tail section of conventional aircraft. In that regard, a lift fan or tail section may be provided in which a stator magnetically levitates a lift fan rotor or tail rotor. The stator may include suspension coils ( 38 ) and drive coils ( 40 ) to eliminate the need for a drive shaft and gears to power the lift fan rotor or tail rotor.

Aircraft and hybrid with magnetic airfoil suspension and drive

A battery system and method of operation are shown. The battery system utilizes a microparticle (15, 16) fuel slurry containing microparticle spheres (15, 16) surrounded by active electrochemical material. In the operation of the battery system, the microparticle spheres are attracted to battery-cell electrode plates (13 and 13b) and held there by a magnetic field. The core of the microparticle spheres (15, 16) and battery-cell electrode plates (13a and 13b) may be permanently magnetic or ferromagnetic in nature. The magnetic field may originate from permanently magnetic materials or be induced using magnetic field windings (14) or the like. The battery system may be recharged by replacing spent microparticle (15, 16) fuel slurry with unspent slurry. In some applications, such as when used to power an electro-motive vehicle, a reserve of unspent microparticle (15, 16) fuel slurry may be stored on-board the vehicle and used to periodically replace spent microparticle (15, 16) fuel slurry during operation. In such applications, when the on-board storage of unspent fuel slurry has been spent, the battery system may be refueled with a new supply of unspent fuel slurry without interrupting operation of the battery.

Magnetic slurry fueled battery system

An aircraft de-icing system is disclosed in which a laser beam generator is positioned on an aircraft, a beam of radiant energy is generated and directed toward the critical surfaces of the aircraft to create a footprint upon the surface of the aircraft, and the beam is manipulated so that the footprint is moved about the aircraft surface for removing ice, snow or water from the critical aircraft surfaces. One or more laser beam generators are preferably disposed remotely from the area to be de-iced, and the beams are preferably reflected from one or more mirrors so that the mirrors may be adjusted to enable the beams to illuminate the critical surfaces of the aircraft. The laser beams preferably have a wavelength that is preferentially reflected by the aircraft surface and absorbed by ice, snow and water, so that the beam heats and removes ice, snow and water from the aircraft surface as the beam's footprint is moved thereabouts.

Onboard aircraft de-icing using lasers

An aircraft ice detection and de-icing system is disclosed in which an aircraft is positioned remotely from a laser beam generator, a beam of radiant energy is reflected from a mirror so that the beam impinges upon and creates a footprint upon a surface of the aircraft and the mirror is manipulated to move the footprint about the aircraft surface. The beam has a wavelength that is preferentially reflected by the aircraft surface and absorbed by ice, snow and water, so the beam heats and removes ice, snow and water from aircraft surfaces as the beam's footprint is moved thereabouts. A remote thermal monitoring system may also be used to monitor temperatures at the aircraft surface for detecting regions experiencing temperature rises at relatively increased rates as the regions are treated with the beam, thereby indicating the presence of ice, snow or water. A visible light may also be used simultaneously to track and indicate movement of the footprint of the treating beam about the aircraft surface.

Aircraft ice detection and de-icing using lasers

The present invention comprises a modular microwave source comprising a novel electromagnetic oscillator based on a modified Blumlein architecture with an integrated antenna In one or more embodiments, the invention comprises a triplate Blumlein in which the plates are configured and arranged to act as a waveguide and antenna In one or more embodiments, high-permittivity dielectric materials are disposed between the center plate and one or both of the top and bottom plates to increase the energy storage and lengthen the duration of a damped sinusoid output In one or more embodiments, photo-conductive semiconductor switches are disposed between the center plate and one or both of the top and bottom plates to act as high-speed switches In one or more embodiments, a plurality of the modular microwave sources of the invention are arranged in an array, creating a compact, tunable, high-power microwave source suitable for mobile applications

William C. Nunnally

Papers

Aircraft and hybrid with magnetic airfoil suspension and drive

Magnetic slurry fueled battery system

Onboard aircraft de-icing using lasers

Aircraft ice detection and de-icing using lasers

Modular microwave source