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 |