Patent application number | Description | Published |
20080246485 | Compact underwater electromagnetic measurement system - An underwater EM measurement system, which is substantially smaller, much simpler to use, and more robust than prior systems, is formed as a sensor package integrated into a single pressure vessel includes two magnetic sensors including induction coils disposed substantially horizontally so as to measure fields in orthogonal directions. The package also includes two electric field sensors including electric potential antennas adapted to couple to a water potential via a capacitive electrode having a conducting material and an electrically insulative layer formed of an insulating material. The capacitive electrode has a capacitance to the medium of greater than 1 mF. Preferably, the insulating material is a metal oxide. | 10-09-2008 |
20090071824 | Integrated Sensing Array for Producing a BioFingerprint of an Analyte - An integrated array of electronic sensing elements outputs a bio-fingerprint of an analyte. System is preferably constructed of as a series of three layers but need not be so arranged. An upper layer defines a fluid volume or analyte chamber; a middle layer contains the sensing elements; and a third layer contains electronic readout elements. The analyte chamber contains an electrolyte and the analyte to be detected. The sensing elements are optimized for maximum detection sensitivity in the minimum response time. The response of each sensing element is read out by a dedicated sensing electrode. Around each electrode is a control ring. The potential of the control ring is set to attract analytes of interest to the sensing elements. | 03-19-2009 |
20090088619 | Self-Locating Sensor Mounting Apparatus - A self-locating mounting apparatus for holding objects such as sensors at specific positions on a subject's head includes a central mount constituted by a plurality of inextensible elements adapted to fit over the top of a subject's head. In addition, the mounting apparatus includes an adjustable circumferential band adapted to circle the subject's head and connect the central mount to inextensible side elements via sliding joints. A plurality of biasing elements provide a force for biasing sensor mounting units on the mounting apparatus against a subject's head, allowing for long-term sensing while minimizing interference forces on the mounting units. Advantageously, the mounting apparatus holds sensors within approximately 5 mm of their desired measurement positions over a range of subject head sizes. | 04-02-2009 |
20090194429 | Apparatus and Method for Sensing a Time Varying Ionic Current in an Electrolytic System - An apparatus and method for sensing time varying ionic current in an electrolytic system having a first fluid chamber and a second fluid chamber separated by a barrier structure is provided, wherein the barrier structure includes thick walls and a substrate having an orifice therein, with the first and second fluid chambers being in communication via the orifice. A potential is applied between electrodes in respective first and second fluid chambers, thus driving an electrical current between them and through the orifice. Total capacitance of the system is less than 10 pF. Analytes are added to one of the first and second fluid chambers and time varying ionic current that passes across the orifice is measured. An amplifier proximal to the barrier structure and electrodes amplifies the ionic current signal. | 08-06-2009 |
20090222216 | System and Method to Improve Accuracy of a Polymer - The sequencing of individual monomers (e.g., a single nucleotide) of a polymer (e.g., DNA, RNA) is improved by reducing the motion of the polymer due to thermally-driven diffusion to reduce the spatial error in the position of the polymer within a measurement device. A major system parameter, such as average translocation velocity or measurement time, is selected based on the characteristics of the sensing system utilized, and an algorithm jointly optimizes the sequencing order error rate and the monomer identification error rate of the system. | 09-03-2009 |
20100148789 | System for Measuring the Electric Potential of a Voltage Source - A non-invasive measurement system ( | 06-17-2010 |
20110162963 | System and Method for Increasing Polymer/Nanopore Interactions - An electrolytic system includes an analyte chamber having an access port for introducing a sample containing a molecules of interest, such as DNA. Electrodes create an electric field along a length of the analyte chamber to drive molecules toward an interaction region containing a nanopore, thereby increasing the arrival rate of molecules at the nanopore. Additional electrodes may be utilized to create an electric field through the nanopore to drive a molecule into the nanopore. A current sensor may be utilized to count, discriminate or characterize the molecules as they interact with the nanopore. Advantageously, system can be utilized for unamplified DNA sequencing. | 07-07-2011 |
20120310543 | System and Method to Improve Sequencing Accuracy of a Polymer - The sequencing of individual monomers (e.g., a single nucleotide) of a polymer (e.g., DNA, RNA) is improved by reducing the motion of the polymer due to thermally-driven diffusion to reduce the spatial error in the position of the polymer within a measurement device. A major system parameter, such as average translocation velocity or measurement time, is selected based on the characteristics of the sensing system utilized, and an algorithm jointly optimizes the sequencing order error rate and the monomer identification error rate of the system. | 12-06-2012 |
20130300419 | Methods, Systems and Apparatuses for Sensing and Measuring the Electric Field within the Earth - Methods, systems, and apparatuses for measuring an electric potential in the earth, which includes a first sensor are disclosed. The first sensor includes a sensing plate for placement in an environment in close proximity to the earth. The sensing plate has an operative capacitive coupling with the earth and measures the earth's electric potential. The sensor also includes a barrier providing electrochemical segregation between the sensing plate and the earth and an amplifier having at least one stage for receiving and amplifying a first signal carrying the potential measured by the sensing plate. The sensor also includes a first connection carrying the first signal from the sensing plate to the amplifier; and a reference voltage for application to the first stage of the amplifier, the reference voltage providing a reference against which the potential measured by the sensing plate is compared. Other embodiments are described and claimed. | 11-14-2013 |
20150219784 | System and Method to Induce an Electromagnetic Field Within the Earth - A system enables a borehole casing to be used to connection with establishing electromagnetic fields within the earth at the depth of formations of interest over a significant surface area. A particular advantage is that a borehole casing can be used as an essential part of the system, without needing to open the borehole. | 08-06-2015 |
Patent application number | Description | Published |
20080237404 | Hydrogen powered aircraft - Disclosed is an aircraft, configured to have a wide range of flight speeds, consuming low levels of power for an extended period of time, while supporting a communications platform with an unobstructed downward-looking view. The aircraft includes an extendable slat at the leading edge of the wing, and a reflexed trailing edge. The aircraft comprises a flying wing extending laterally between two ends and a center point. The wing is swept and has a relatively constant chord. The aircraft also includes a power module configured to provide power via a fuel cell. The fuel cell stores liquid hydrogen as fuel, but uses gaseous hydrogen in the fuel cell. A fuel tank heater is used to control the boil-rate of the fuel in the fuel tank. The fuel cell compresses ambient air for an oxidizer, and operates with the fuel and oxidizer at pressures below one atmosphere. The aircraft of the invention includes a support structure including a plurality of supports, where the supports form a tetrahedron that affixes to the wing. | 10-02-2008 |
20080241621 | Energy storage system - A closed loop energy storage system configured with a hydrogen tank, an oxygen tank, a fuel cell stack and an electrolyzer. A heat exchanger freeze-dries the hydrogen and oxygen prior to their storage in their respective tanks. The heat exchanger also uses excess fuel cell heat to preheat streams of hydrogen and oxygen coming from the tanks. Phase separators serve both to separate water from hydrogen and oxygen, and to store the water. A thermal management system encloses all the system components except the tanks. An airfoil-shaped shell covers the system, and the larger of the two tanks extends substantially across the shell at its point of greatest camber thickness. The tanks are composed of polymer liners integral with composite shells. | 10-02-2008 |
20090213781 | High altitude platform deployment system - A communication system for supporting communications with a target market area. The system includes one or more solar-powered aircraft maintained in, or successively passing through, flight stations or flight patterns around the market area. Each of the aircraft targets limited beamwidth communication antennas on a substantial portion of the target market area. The control system is configured to fly selective flight patterns depending on the aircraft characteristics and the flight conditions. The flight patterns may emphasize high-power-generation patterns such as flying away from the sun for aircraft with wing-mounted solar cells. | 08-27-2009 |
20100055512 | ENERGY STORAGE SYSTEM - A closed loop energy storage system configured with a hydrogen tank, an oxygen tank, a fuel cell stack and an electrolyzer. A heat exchanger freeze-dries the hydrogen and oxygen prior to their storage in their respective tanks. The heat exchanger also uses excess fuel cell heat to preheat streams of hydrogen and oxygen coming from the tanks. Phase separators serve both to separate water from hydrogen and oxygen, and to store the water. A thermal management system encloses all the system components except the tanks. An airfoil-shaped shell covers the system, and the larger of the two tanks extends substantially across the shell at its point of greatest camber thickness. The tanks are composed of polymer liners integral with composite shells. | 03-04-2010 |
20110039171 | Energy storage system - A closed loop energy storage system configured with a hydrogen tank, an oxygen tank, a fuel cell stack and an electrolyzer. A heat exchanger freeze-dries the hydrogen and oxygen prior to their storage in their respective tanks. The heat exchanger also uses excess fuel cell heat to preheat streams of hydrogen and oxygen coming from the tanks. Phase separators serve both to separate water from hydrogen and oxygen, and to store the water. A thermal management system encloses all the system components except the tanks. An airfoil-shaped shell covers the system, and the larger of the two tanks extends substantially across the shell at its point of greatest camber thickness. The tanks are composed of polymer liners integral with composite shells. | 02-17-2011 |
20120104163 | Hydrogen powered aircraft - Disclosed is an aircraft, configured to have a wide range of flight speeds, consuming low levels of power for an extended period of time, while supporting a communications platform with an unobstructed downward-looking view. The aircraft includes an extendable slat at the leading edge of the wing, and a reflexed trailing edge. The aircraft comprises a flying wing extending laterally between two ends and a center point. The wing is swept and has a relatively constant chord. The aircraft also includes a power module configured to provide power via a fuel cell. The fuel cell stores liquid hydrogen as fuel, but uses gaseous hydrogen in the fuel cell. A fuel tank heater is used to control the boil-rate of the fuel in the fuel tank. The fuel cell compresses ambient air for an oxidizer, and operates with the fuel and oxidizer at pressures below one atmosphere. | 05-03-2012 |
20130034783 | Energy storage system - A closed loop energy storage system configured with a hydrogen tank, an oxygen tank, a fuel cell stack and an electrolyzer. A heat exchanger freeze-dries the hydrogen and oxygen prior to their storage in their respective tanks. The heat exchanger also uses excess fuel cell heat to preheat streams of hydrogen and oxygen coming from the tanks. Phase separators serve both to separate water from hydrogen and oxygen, and to store the water. A thermal management system encloses all the system components except the tanks. An airfoil-shaped shell covers the system, and the larger of the two tanks extends substantially across the shell at its point of greatest camber thickness. The tanks are composed of polymer liners integral with composite shells. | 02-07-2013 |
Patent application number | Description | Published |
20100181858 | FLUX CONCENTRATOR FOR IRONLESS MOTORS - In one possible embodiment, a magnet array for a motor is provided which has an array of permanent magnets being arranged such that flux from the permanent magnets reinforce on one side of the array and substantially cancel on an opposite side of the array, the array further includes flux concentrators located at poles on the reinforcing side of the array. | 07-22-2010 |
20100187237 | Cryogenic Liquid Tank - A hydrogen storage tank for a hydrogen fueled aircraft. The tank has a wall made of layers of aerogel sections around a hard shell layer, sealed within a flexible outer layer, and having the air removed to form a vacuum. The periphery of each layer section abuts other sections of that layer, but only overlies the periphery of the sections of other layers at individual points. The wall is characterized by a thermal conductivity that is lower near its gravitational top than its gravitational bottom. The tank has two exit passageways, one being direct, and the other passing through a vapor shield that extends through the wall between two layers of aerogel. A control system controls the relative flow through the two passages to regulate the boil-off rate of the tank. | 07-29-2010 |
20100187922 | MOTOR AIR FLOW COOLING - In one possible embodiment, an aircraft electric motor cooling system is provided having an airflow path through a spinner which includes a first airflow path between an inner rotor and a stator, a second airflow path between an outer rotor the stator and a third airflow path along an outer surface of the outer rotor. | 07-29-2010 |
20100192890 | Cold fuel cooling of intercooler and aftercooler - A high-altitude aircraft powerplant including an engine, a two-stage turbocharger having an intercooler and an aftercooler, a cryogenic hydrogen fuel source, and a cooling system including a hydrogen heat exchanger. Aided by a ram-air cooler that cools a coolant to a near-ambient temperature, the heat exchanger is configured to heat the hydrogen using the coolant, and to cool the coolant to a temperature well below the ambient temperature during high-altitude flight. The intercooler and aftercooler use the sub-ambient temperature coolant, as does a separate sensor. The ram-air cooler includes a front portion and a rear portion. The cooling system includes three cooling loops which respectively incorporate only the front portion, only the rear portion, and both portions of the ram-air cooler. | 08-05-2010 |
20100194218 | STATOR WINDING HEAT SINK CONFIGURATON - In one possible implementation, a motor is provided including a rotor and a stator. Front cooling fins are thermally coupled to a front of the stator, and rear cooling fins are thermally coupled to a rear portion of the stator. The winding is between the front and rear cooling fins. | 08-05-2010 |
20100194231 | COMPRESSED MOTOR WINDING - In one possible implementation, a method for forming a motor winding is provided which includes compressing a Litz wire to form a compacted Litz wire and forming the winding with the compacted Litz wire. In one possible embodiment, a motor winding is provided that has a high density multi-conductor wire bundle comprises of compacted Litz wire. | 08-05-2010 |
20100308160 | Air Vehicle Flight Mechanism and Control Method - Heavier-than-air, aircraft having flapping wings, e.g., ornithopters, where angular orientation control is effected by variable differential sweep angles of deflection of the flappable wings in the course of sweep angles of travel and/or the control of variable wing membrane tension. | 12-09-2010 |
20130048242 | HEAT TRANSFER SYSTEM FOR AIRCRAFT STRUCTURES - A heat transfer system is provided by the present disclosure that includes, in one form, a structural member having an upper skin, a lower skin, and a foam core disposed between the upper skin and the lower skin. At least one heat conducting array extends through the foam core and between the upper skin and the lower skin, the heat conducting array defining at least one upper cap, at least one lower cap, and a wall portion extending between the upper cap and the lower cap, the upper cap being disposed proximate a heat source. A heat conducting spreader is disposed between the lower cap of the heat conducting array and the lower skin of the structural member. | 02-28-2013 |
20130074812 | Cold fuel cooling of intercooler and aftercooler - A high-altitude aircraft powerplant including an engine, a two-stage turbocharger having an intercooler and an aftercooler, a cryogenic hydrogen fuel source, and a cooling system including a hydrogen heat exchanger. Aided by a ram-air cooler that cools a coolant to a near-ambient temperature, the heat exchanger is configured to heat the hydrogen using the coolant, and to cool the coolant to a temperature well below the ambient temperature during high-altitude flight. The intercooler and aftercooler use the sub-ambient temperature coolant, as does a separate sensor. The ram-air cooler includes a front portion and a rear portion. The cooling system includes three cooling loops which respectively incorporate only the front portion, only the rear portion, and both portions of the ram-air cooler. | 03-28-2013 |
20130168493 | Air Vehicle Flight Mechanism and Control Method - Heavier-than-air, aircraft having flapping wings, e.g., ornithopters, where angular orientation control is effected by variable differential sweep angles of deflection of the flappable wings in the course of sweep angles of travel and/or the control of variable wing membrane tension. | 07-04-2013 |
20140145529 | MOTOR AIR FLOW COOLING - In one possible embodiment, an aircraft electric motor cooling system is provided having an airflow path through a spinner which includes a first airflow path between an inner rotor and a stator, a second airflow path between an outer rotor the stator and a third airflow path along an outer surface of the outer rotor. | 05-29-2014 |
20150014475 | Vertical Takeoff and Landing (VTOL) Air Vehicle - A flight control apparatus for fixed-wing aircraft includes a first port wing and first starboard wing, a first port swash plate coupled between a first port rotor and first port electric motor, the first port electric motor coupled to the first port wing, and a first starboard swash plate coupled between a first starboard rotor and first starboard electric motor, the first starboard electric motor coupled to the first starboard wing. | 01-15-2015 |
20150115097 | Air Vehicle Flight Mechanism and Control Method - Heavier-than-air, aircraft having flapping wings, e.g., ornithopters, where angular orientation control is effected by variable differential sweep angles of deflection of the flappable wings in the course of sweep angles of travel and/or the control of variable wing membrane tension. | 04-30-2015 |
20150266146 | METHOD OF MANUFACTURING A HEAT TRANSFER SYSTEM FOR AIRCRAFT STRUCTURES - A method of manufacturing a heat transfer system is provided that includes preparing a heat conducting array by perforating at least a portion of the heat conducting array, placing the heat conducting array around foam elements, and forming the structural assembly under heat and pressure. A material of the foam elements extends through the perforated portion of the heat conducting array during the forming step. | 09-24-2015 |
20150303755 | COMPRESSED MOTOR WINDING - In one possible embodiment, a motor winding is provided having a high density multi-conductor wire bundle with a compacted Litz wire bundle. The compacted Litz wire bundle has a serpentine configuration with a central portion having compacted Litz wire and end turns having non-compacted Litz wire. | 10-22-2015 |
20150307180 | HEAT TRANSFER SYSTEM FOR AIRCRAFT STRUCTURES - A heat transfer system for use within an avionics bay of an aircraft is provided by the present disclosure that includes, in one form, an aircraft panel comprising an upper skin, a lower skin, and a foam core disposed between the upper skin and the lower skin. At least one heat conducting array extends through the foam core and between the upper skin and the lower skin, the heat conducting array defining at least one upper cap, at least one lower cap, and a wall portion extending between the upper cap and the lower cap, the upper cap being disposed proximate avionics within the avionics bay. A heat conducting spreader is disposed between the lower cap of the heat conducting array and the lower skin of the aircraft panel. | 10-29-2015 |