Popelka
Brian Popelka, Salt Lake City, UT US
Patent application number | Description | Published |
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20090012881 | SYSTEM AND METHOD FOR IMPROVED MANAGEMENT OF SELLER LISTINGS ON E-COMMERCE WEBSITES - A system and method providing improved management of product listings on an e-commerce website by allowing sellers to define rules or conditions that automatically adjust a product's listing price based upon a triggering event. The triggering event may be the expiration of a pre-defined time period. The listing price of a product can be automatically reduced in the event that the product does not sell within a certain time frame. Further, sellers are immediately notified of an offer to purchase a listed product. | 01-08-2009 |
David Popelka, Colleyville, TX US
Patent application number | Description | Published |
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20100009764 | Rotary-Wing Aircraft Torque Coupling with Pad Bearings - A torque coupling for a rotor head of a rotary-wing aircraft is configured for rotation with a mast and for causing rotation of an attached yoke. The coupling has trunnions that rotate with the mast and extend generally radially. Pad-bearing assemblies each have a central member coupled to one of the trunnions with a laminated spherical bearing and have laminated pad bearings affixed to opposing sides of the central member. The laminated bearings have alternating rigid and elastomeric layers. A bearing mount is affixed to each pad bearing and is connected to a yoke for rotating the yoke with the mast. The pad-bearing assemblies allow for relative motion between each central member and the associated trunnion and between each central member and the bearing mounts through elastic shear deformation, and this allows for gimballing of the attached yoke relative to the mast. | 01-14-2010 |
20130164129 | Hub Assembly with Grease Lubricated Roller Bearing and Tension-Torsion Strap - A rotary system and method to control feathering and centrifugal forces of a rotor blade during flight. The rotary system having a hub assembly, which includes a hollow yoke arm to receive a spindle section of the rotor blade. A tension-torsion strap extends through the hollow yoke arm and couples the rotor blade and the hub assembly. The method includes allowing the spindle section of the rotor blade to pivot within the hollow yoke arm and controlling rotational and centrifugal movement of the rotor blade with the tension-torsion strap. | 06-27-2013 |
20130216384 | Compact Rotorcraft Dual-Element Spherical Elastomeric Centrifugal-Force Bearing Assembly - A rotary system includes a retention member and a flexible yoke having an opening forming a bridge. The rotary system is further provided with two bearing assemblies, a first bearing assembly extending through the opening of the yoke and configured to secure a rotor blade to the retention member and a second bearing assembly extending through the opening of the flexible yoke and configured to secure the rotor blade to the bridge. The second bearing element includes a bearing element having a first surface forming a spherical contouring and an opposing integral second surface forming a conical contouring. | 08-22-2013 |
David A. Popelka, Colleyville, TX US
Patent application number | Description | Published |
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20080247876 | Soft In-Plane Tiltrotor Hub - A rotor hub assembly for a rotary-wing aircraft has a central member and a plurality of blade grips adapted for attaching rotor blades to the central member. The blade grips are pivotally attached to the central member and are capable of pivoting about a pivot axis generally normal to a plane of rotation of the blades. The pivoting allows for in-plane motion of the blades relative to the central member. A damper is operably connected to each blade grip for damping the in-plane motion of the associated blade, each damper being selectively switchable between at least two spring rates. | 10-09-2008 |
20100021301 | Step-Over Blade-Pitch Control System - A pitch control system for blades on a rotor of an aircraft has a gimballing rotor hub ( | 01-28-2010 |
20100209242 | Rotor Hub Vibration Attenuator - A vibration attenuator for an aircraft has at least one weight mounted in a rotating system of a rotor hub of the aircraft, each weight being rotatable about an axis of rotation of the hub relative to the hub and to each other weight. Drive means are provided for rotating each weight about the axis of rotation at a selected speed for creating oscillatory shear forces that oppose and attenuate rotor-induced vibrations having a selected frequency. | 08-19-2010 |
20110194934 | Rotor Hub Vibration Attenuator - A vibration attenuator for an aircraft has at least one weight mounted in a rotating system of a rotor hub of the aircraft, each weight being rotatable about an axis of rotation of the hub relative to the hub and to each other weight. Drive means are provided for rotating each weight about the axis of rotation at a selected speed for creating oscillatory shear forces that oppose and attenuate rotor-induced vibrations having a selected frequency. A vertically oriented vibration attenuator is configured to oppose and attenuate vertical rotor induced oscillatory forces that would otherwise travel vertical down the rotor mast and into the airframe. | 08-11-2011 |
20120230823 | Dual Spring Rate Damper - A rotor hub and method to dampen a force exerted on a rotor hub by a rotor blade during flight. The rotor hub including a central member rotatably coupled to a rotor mast, a blade grip rigidly attached to a blade and movably coupled to the central member, and an adjustable damper operably associated with the blade grip. The method includes damping the force exerted on the rotor hub with the adjustable damper and selectively adjusting the adjustable damper between a first spring rate and a second spring rate. | 09-13-2012 |
20120305698 | Method and Apparatus for Actively Manipulating Aerodynamic Surfaces - A method and apparatus is provided, including an actuator system that may be connected to a wing frame for controlling an active element. The actuator system may include sliding elements movable along an axis parallel to the span-wise axis of the wing. The sliding elements may be connected to fixed elements and a crank element, the crank element generally comprising a beam element and a cross-axis flexure pivot element. The beam element may be offset from the pivot element so that the crank element is rotatable about the pivot element with a negative stiffness under an external force that tends to pull the sliding elements away from the fixed elements. | 12-06-2012 |
20130084183 | DUAL SERIES DAMPER SYSTEM - A dual series damper includes a fluid damper portion and a elastomeric damper portion. The fluid damper portion includes a first housing, a first connection member, and a piston coupled to the first connection member. The piston divides an interior of the first housing into a first fluid chamber and a second fluid chamber. The piston has a fluid passage in the piston, the fluid passage being configured to provide fluid communication between the first fluid chamber and the second fluid chamber. The elastomeric damper portion includes a second housing, a second connection member coupled to the second housing, and an elastomer between the first housing and the second housing. When a lead/lag force is introduced to the dual series damper, the fluid damper portion behaves rigidly so that the elastomeric damper portion dampens the lead/lag oscillation. | 04-04-2013 |
20130105637 | Active Prop Rotor Stability System | 05-02-2013 |
20130149151 | Multiple-Yoke Main Rotor Assembly - The present application includes a main rotor assembly for an aircraft. The rotor assembly has a main rotor mast configured for rotation about a mast axis and two yokes pivotally connected to the mast for rotation therewith about the mast axis. Each yoke is independently pivotable relative to the mast about at least one flap axis that is generally perpendicular to the mast axis. In at least one embodiment, a torque splitter connects the yokes and allows for limited rotation of the yokes relative to each other about the mast axis. Each yoke is configured for the attachment of rotor blades extending generally radially relative to the mast axis. | 06-13-2013 |
20130189098 | System and Method of Harvesting Power with a Rotor Hub Damper - The system and method of the present application relate to a lead/lag damper for a rotorcraft. The lead/lag damper is configured to harvest power from the lead/lag oscillatory motions of rotor blades with an electromagnetic linear motor/generator. Further, the lead/lag damper is configured to treat the lead/lag motions with the electromagnetic linear motor/generator. The system and method is well suited for use in the field of aircraft, in particular, helicopters and other rotary wing aircraft. | 07-25-2013 |
20130287576 | Aircraft Rotor with Discrete Flap Hinge - An aircraft rotor assembly has upper and lower hub plates adapted to be mounted to a central rotor mast for rotation therewith. A plurality of radial arms is connected to at least two flap bearings mounted between the hub plates and forming a discrete flap hinge, each flap hinge defining a flap axis and allowing rotation of the associated arm relative to the hub plates and about the corresponding flap axis. Each of a plurality of blade grips is rotatably connected to one of the arms for rotation about a pitch axis and adapted for mounting of a blade to each blade grip, such that each blade is capable of rotation with the grip about the pitch axis and capable of rotation together with the corresponding arm relative to the hub plates and about the corresponding flap axis. | 10-31-2013 |
20140286772 | ROTOR HUB VIBRATION ATTENUATOR - A vibration attenuator for an aircraft has at least one weight mounted in a rotating system of a rotor hub of the aircraft, each weight being rotatable about an axis of rotation of the hub relative to the hub and to each other weight. Drive means are provided for rotating each weight about the axis of rotation at a selected speed for creating oscillatory shear forces that oppose and attenuate rotor-induced vibrations having a selected frequency. A vertically oriented vibration attenuator is configured to oppose and attenuate vertical rotor induced oscillatory forces that would otherwise travel vertical down the rotor mast and into the airframe. | 09-25-2014 |
20140360830 | ROTOR HUB VIBRATION ATTENUATOR - A vibration attenuator for an aircraft has at least one weight mounted in a rotating system of a rotor hub of the aircraft, each weight being rotatable about an axis of rotation of the hub relative to the hub and to each other weight. Drive means are provided for rotating each weight about the axis of rotation at a selected speed for creating oscillatory shear forces that oppose and attenuate rotor-induced vibrations having a selected frequency. A vertically oriented vibration attenuator is configured to oppose and attenuate vertical rotor induced oscillatory forces that would otherwise travel vertical down the rotor mast and into the airframe. A vibration attenuator having weights rotating about separate axes offset from each other. | 12-11-2014 |
David J. Popelka, Alpharetta, GA US
Patent application number | Description | Published |
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20110193649 | INTEGRATED CIRCULATORS SHARING A CONTINUOUS CIRCUIT - The present invention is directed to a circuit assembly that includes an integrated circulator assembly. The circuit assembly has a first substrate, which contains a continuous circuit trace that includes a circulator component from the circulator assembly and at least one electrical component from the circuit assembly. A second substrate is disposed beneath the first substrate and includes a cladding on one surface. The second substrate contains an aperture that accepts a ferrite element, which is axially aligned with the circulator component of the circuit trace. A conductive material is placed across the ferrite element so that it forms a continuous ground plane with the cladding, which is common to the entire circuit trace. The circulator assembly also contains a magnet bonded to the ferrite element. The circulator assembly may also include a yoke disposed below the magnet to shield the circulator from external magnetic fields. | 08-11-2011 |
20130291381 | INTEGRATED CIRCULATORS SHARING A CONTINUOUS CIRCUIT - The present invention is directed to a circuit assembly that includes an integrated circulator assembly. The circuit assembly has a first substrate, which contains a continuous circuit trace that includes a circulator component from the circulator assembly and at least one electrical component from the circuit assembly. A second substrate is disposed beneath the first substrate and includes a cladding on one surface. The second substrate contains an aperture that accepts a ferrite element, which is axially aligned with the circulator component of the circuit trace. A conductive material is placed across the ferrite element so that it forms a continuous ground plane with the cladding, which is common to the entire circuit trace. The circulator assembly also contains a magnet bonded to the ferrite element. The circulator assembly may also include a yoke disposed below the magnet to shield the circulator from external magnetic fields. | 11-07-2013 |
Gerald R. Popelka, Menlo Park, CA US
Patent application number | Description | Published |
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20090216108 | Real-time magnetic resonance imaging and peripheral arterial tone in sleep apnea diagnosis - Obstructive sleep apnea diagnosis based on peripheral arterial tone (PAT) and real-time magnetic resonance imaging (MRI) is provided. PAT and other physiological data are used to identify respiratory events experienced by a subject with obstructive sleep apnea. MRI images are recorded at least during the respiratory events to identify airway obstructions responsible for the sleep apnea events. The MRI images are recorded in real-time at a high frame rate during the sleep apnea events. The PAT signals and MRI images are collected while the subject is in a sleep state. PAT signals can also be used to identify sleep apnea events and trigger an MRI device to begin recording, thereby reducing the costs associated with recording extraneous and large amounts of MRI data. | 08-27-2009 |
Paul Popelka, Cupertino, CA US
Patent application number | Description | Published |
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20100287142 | ACCESSING, COMPRESSING, AND TRACKING MEDIA STORED IN AN OPTICAL DISC STORAGE SYSTEM - Methods, systems, and computer readable media are provided for accessing and compressing data stored in a media library, as well as tracking optical media with media tags and cartridge manifests within a library. In one embodiment, a simulation layer of a hybrid storage appliance allows libraries of optical media with write-once read-many (WORM) properties to look like logical block devices with non-WORM characteristics. In another embodiment, data from a user's files is compressed by the media library appliance in chunks in such a way that coarse granularity seeking is possible within a compressed user file. In another embodiment, a media cloud is used by a hybrid storage appliance to seamlessly recover from failures in optical media, library robotics, optical drives, and network connections during the creation, recovery, and distribution of data. In another embodiment, cartridge manifests and media tags are used to track optical media within a library. | 11-11-2010 |
Rolf Popelka, Moerfelden-Walldorf DE
Patent application number | Description | Published |
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20100189586 | Pump Housing - A pump housing, in particular a vane cell pump housing, having a suction connection point, from which a suction channel emerges which opens with a suction-channel opening into a receiving chamber in the pump housing, and having a pressure connection point, from which a pressure channel emerges which opens at a pressure-channel opening into the receiving chamber. The invention is distinguished by the fact that the suction connection point, the pressure connection point, the suction-channel opening and/or the pressure-channel opening are/is arranged in such a way that a minimum level of a conveying fluid which is present in the receiving chamber is not undershot in different installation situations. | 07-29-2010 |