Andryukov
Alexander Andryukov, Simi Valley, CA US
Patent application number | Description | Published |
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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 |
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 |
20140158821 | Air Vehicle Flight Mechanism and Control Method for Non-Sinusoidal Wing Flapping - A flapping wing driving apparatus includes at least one crank gear capstan rotatably coupled to a crank gear, the at least one crank gear capstan disposed radially offset from a center of rotation of the crank gear; a first wing capstan coupled to a first wing, the first wing capstan having a first variable-radius drive pulley portion; and a first drive linking member configured to drive the first wing capstan, the first drive linking member windably coupled between the first variable-radius drive pulley portion and one of the at least one crank gear capstan; wherein the first wing capstan is configured to non-constantly, angularly rotate responsive to a constant angular rotation of the crank gear. | 06-12-2014 |
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 |
Oleksandr Andryukov, Simi Valley, CA US
Patent application number | Description | Published |
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20110315817 | SYSTEMS AND DEVICES FOR REMOTELY OPERATED UNMANNED AERIAL VEHICLE REPORT-SUPPRESSING LAUNCHER WITH PORTABLE RF TRANSPARENT LAUNCH TUBE - An unmanned aerial vehicle (UAV) launch tube that comprises a tethered sabot configured to engage a UAV within a launcher volume defined by an inner wall, the tethered sabot dimensioned to provide a pressure seal at the inner wall and tethered to the inner wall, and wherein the tethered sabot is hollow having an open end oriented toward a high pressure volume and a tether attached within a hollow of the sabot and attached to the inner wall retaining the high pressure volume or attach to the inner base wall. A system comprising a communication node and a launcher comprising an unmanned aerial vehicle (UAV) in a pre-launch state configured to receive and respond to command inputs from the communication node. | 12-29-2011 |
20120001020 | SYSTEMS AND DEVICES FOR REMOTELY OPERATED UNMANNED AERIAL VEHICLE REPORT-SUPPRESSING LAUNCHER WITH PORTABLE RF TRANSPARENT LAUNCH TUBE - An unmanned aerial vehicle (UAV) launch tube that comprises a tethered sabot configured to engage a UAV within a launcher volume defined by an inner wall, the tethered sabot dimensioned to provide a pressure seal at the inner wall and tethered to the inner wall, and wherein the tethered sabot is hollow having an open end oriented toward a high pressure volume and a tether attached within a hollow of the sabot and attached to the inner wall retaining the high pressure volume or attach to the inner base wall. A system comprising a communication node and a launcher comprising an unmanned aerial vehicle (UAV) in a pre-launch state configured to receive and respond to command inputs from the communication node. | 01-05-2012 |
Vladislav Andryukov, Kent, WA US
Patent application number | Description | Published |
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20160023431 | FABRIC JACKETED UNIDIRECTIONAL NOODLE - A composite, radius filler noodle for a co-cured spar or stringer used in aircraft construction has a unidirectional composite core and pluralities of pre-preg fabric strips stacked in layers surrounding the core. | 01-28-2016 |
Vladislay Andryukov, Kent, WA US
Patent application number | Description | Published |
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20090294589 | METHODS AND APPARATUS FOR AN INTEGRATED AERODYNAMIC PANEL - An integrated aerodynamic panel—e.g., for a trailing edge or leading edge of an aircraft aerodynamic surface—includes a first panel region defining inner and outer mold lines, and a second panel region contiguous with and extending from the first panel region in a tapering fashion. A splice plate region extends from the second panel region and includes an edge band region configured to accept a fastener. A filler region (e.g., a SYNCORE or fiberglass structure) adjacent the second panel region has an exposed surface substantially flush with the outer mold line. | 12-03-2009 |