子分类：
| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 161 | METHODS AND APPARATUS FOR UNMANNED AERIAL VEHICLE LANDING AND LAUNCH | US15804609 | 2017-11-06 | US20180065759A1 | 2018-03-08 | Jeff MICHALSKI; Michael FOLEY |
| An unmanned aerial vehicle (UAV), a stand for launching, landing, testing, refueling and recharging a UAV, and methods for testing, landing and launching the UAV are disclosed. Further, embodiments may include transferring a payload onto or off of the UAV, and loading flight planning and diagnostic maintenance information to the UAV. | ||||||
| 162 | Launch tube restraint system for unmanned aerial vehicle (UAV) | US15292908 | 2016-10-13 | US09873526B2 | 2018-01-23 | Guan H Su; Marcos Henry Rodriguez |
| An unmanned aerial launch vehicle (UAV) launch apparatus is disclosed that includes a UAV (400) having an exterior surface, an aerial vehicle (AV) tab (510) extending from the exterior surface, a tube (440) containing the UAV (400), the tube (440) including a tab stop (515) configured to controllably hinder travel of the AV tab (510) past the tab stop (515), and a pair of opposing tab guides (700, 705) configured to position the AV tab (510) for travel over the tab stop (515). | ||||||
| 163 | LOCKING LINE CAPTURE DEVICES FOR UNMANNED AIRCRAFT, AND ASSOCIATED SYSTEMS AND METHODS | US15194492 | 2016-06-27 | US20170369185A1 | 2017-12-28 | Matthew Grubb |
| Locking line capture devices for unmanned aircraft, and associated systems and methods are disclosed herein. A representative system includes a line capture body having a line slot with an open end and closed end, and a retainer positioned proximate the line slot and movable between first position in which the retainer blocks access to the line slot and a second position in which the retainer allows access to the line slot. A locking device is operably coupled between the capture body and the retainer and is movable between an unlocked position to allow movement of the retainer between the first and second positions, and a locked position to block such movement. A release device is operably coupled to the locking device and movable between a secured position with the locking device secured in the locked position, and a released position with the locking device movable between the locked and unlocked positions. | ||||||
| 164 | SPLIT CHORD DEPLOYABLE WING | US15161261 | 2016-05-22 | US20170336184A1 | 2017-11-23 | Paul A. Merems |
| A split-chord deployable wing for aerial vehicles such as missiles, UAVs, MALDs and SDBs that require both longer wing span and increased chord length. Such split-chord deployable wings must address unique problems such as synchronized deployment and integrity of the deployed wing to both vertical and sheer loads. Each wing comprises a pair of wing sections stowed fore and aft along the fuselage. Complementary gear teeth synchronize deployment of the wing sections. A deployment mechanism synchronizes deployment of the wings. Complementary tongue and groove surface portions of the wing sections progressive engage as the wing sections pivot away from the fuselage. The surface portions are segmented so that tongue segments are nested within complementary groove segments to provide both vertical and sheer stability. | ||||||
| 165 | APPARATUS AND METHOD FOR LAUNCH AND RECOVERY OF AN UNMANNED AERIAL VEHICLE | US15521892 | 2014-11-27 | US20170320592A1 | 2017-11-09 | Xujian CHEN; Leon Choon Seng TAN; Chian Poh LAM |
| An apparatus for launch and recovery of an Unmanned Aerial Vehicle (UAV), a method for launching a UAV, a method for recovering a UAV and a kit of parts for launch and recovery of a UAV. The apparatus comprises a boom having a center member for receiving the UAV, and first and second arm members extending outwardly and upwardly from the center member, wherein the boom is configured to be lifted to a predetermined height into the air from a reference point; and wherein the boom is movable in the air to an operating position forward of the reference point. | ||||||
| 166 | Short takeoff and landing aircraft | US14231003 | 2014-03-31 | US09771163B2 | 2017-09-26 | Rich P. Ouellette |
| Short takeoff and landing aircraft are disclosed. An example fixed wing aircraft includes a primary power source to provide power to a propulsion unit, a secondary power source to provide power to the propulsion unit, and a detachable power coupling to transfer power to the secondary power source from a source external to the fixed wing aircraft during takeoff. | ||||||
| 167 | SYSTEM AND METHOD FOR DATA BACKUP USING UNMANNED AERIAL VEHICLE (UAV) | US15464449 | 2017-03-21 | US20170270314A1 | 2017-09-21 | Yuriy Tsybrovskyy; Stanislav S. Protasov; Serguei M. Beloussov; Mark Shmulevich |
| Disclosed are systems, methods and computer program products for performing data backup using an unmanned aerial vehicle (UAV). An example method includes in response to detecting a data backup request from a user device, determining a geographic location of the user device and dispatching the UAV to the geographic location; controlling the UAV to obtain user data from the user device; and controlling the UAV to navigate to a data center to back up the obtained user data onto a cloud storage. | ||||||
| 168 | STITCHED IMAGE | US15274060 | 2016-09-23 | US20170228904A1 | 2017-08-10 | Dennis Bushmitch; Michael Badger |
| Various embodiments associated with a composite image are described. In one embodiment, a handheld device comprises a launch component configured to cause a launch of a projectile. The projectile is configured to capture a plurality of images. Individual images of the plurality of images are of different segments of an area. The system also comprises an image stitch component configured to stitch the plurality of images into a composite image. The composite image is of a higher resolution than a resolution of individual images of the plurality of images. | ||||||
| 169 | Surveillance system | US14370178 | 2012-12-05 | US09725172B2 | 2017-08-08 | Clyde Warsop; Andrew Julian Press; Alan Geraint Davies |
| The invention relates to a launched aerial surveillance vehicle, more specifically to a grenade or under-slung grenade launcher (UGL) aerial surveillance vehicle, a surveillance system and methods of providing rapid aerial surveillance.The vehicle once deployed is capable of autonomous flight paths, with basic inputs to change the circular flight paths, so as to build up surveillance for an area of interest. The vehicle comprises at least one optical sensor, which may be IR or visible range, to survey the area of interest, and feed the images back to at least one remote user. | ||||||
| 170 | Methods for launching and landing an unmanned aerial vehicle | US14236305 | 2013-12-13 | US09696725B2 | 2017-07-04 | Ming-yu Wang |
| Methods and apparatus are provided for launching and landing unmanned aerial vehicles (UAVs) including multi-rotor aircrafts. The methods and apparatus disclosed herein utilize positional change of the UAV, visual signal, or other means to effect the launch or landing. The methods and apparatus disclosed herein are user friendly, particularly to amateur UAV users lacking practice of operating a UAV. | ||||||
| 171 | METHOD AND DEVICE FOR RETRIEVING AND FLYING UNMANNED AERIAL VEHICLE IN HANDHELD MANNER | US15115760 | 2016-01-11 | US20170176992A1 | 2017-06-22 | Mengqiu WANG; Tong ZHANG; Qicheng LI; Jia LU; Lixin LIU |
| A method and a device for flying an unmanned aerial vehicle in a handheld manner and an unmanned aerial vehicle are provided. The method includes: judging whether the unmanned aerial vehicle is triggered to enter a flight standby state; determining whether the unmanned aerial vehicle is in a handheld flat-laying state for a predetermined time period when it enters the flight standby state; and comparing a state parameter of the unmanned aerial vehicle with the state parameter thereof at a previous time instant to judge whether it is released when it is in the handheld flat-laying state, and controlling its rotor wing to rotate for flight when the unmanned aerial vehicle is released. The method is easy to implement, the elimination of the remote control results in a cost saving and the user does not need to operate the remote control. | ||||||
| 172 | Combined submersible vessel and unmanned aerial vehicle | US14944482 | 2015-11-18 | US09616997B2 | 2017-04-11 | Robert Parks; Adam Woodworth; Tom Vaneck; Justin McClellan |
| A combined submersible vessel and unmanned aerial vehicle preferably includes a body structure, at least one wing structure, at least one vertical stabilizer structure, and at least one horizontal stabilizer structure. A propulsion system is coupled to the body structure and is configured to propel the flying submarine in both airborne flight and underwater operation. Preferably, the propulsion system includes a motor, a gearbox coupled to the motor and configured to receive power generated by the motor and provide variable output power, a drive shaft coupled to the gearbox and configured to transfer the variable output power provided by the gearbox, and a propeller coupled to the drive shaft and configured to accept power transferred to it from the drive shaft. The propeller is further configured to rotate and propel the flying submarine in both an airborne environment and in an underwater environment. | ||||||
| 173 | PRE-FLIGHT SELF TEST FOR UNMANNED AERIAL VEHICLES (UAVs) | US15364852 | 2016-11-30 | US20170081045A1 | 2017-03-23 | Charles Calvin Byers; Gonzalo Salgueiro |
| In one embodiment, a controller instructs an unmanned aerial vehicle (UAV) docked to a landing perch to perform a pre-flight test operation of a pre-flight test routine. The controller receives sensor data associated with the pre-flight test operation from one or more force sensors of the landing perch, in response to the UAV performing the pre-flight test operation. The controller determines whether the sensor data associated with the pre-flight test operation is within an acceptable range. The controller causes the UAV to launch from the landing perch based in part on a determination that UAV has passed the pre-flight test routine. | ||||||
| 174 | LAUNCH CANISTER WITH AIR BAG RAM | US14845615 | 2015-09-04 | US20170066543A1 | 2017-03-09 | Russell M. SYLVIA |
| A payload launch system that uses an inflatable air bag ram to launch a payload, such as an unmanned aerial vehicle, from a launch chamber of a launch tube. The air bag ram seals with the interior surface of the launch tube to isolate a dump valve that controls the flow of compressed gas from a gas storage chamber into the air bag ram. The air bag ram sealing with the interior surface of the launch tube isolates the dump valve, both pre-launch and post-launch, from any water or debris carried in with water in which the payload launch system is disposed | ||||||
| 175 | Pre-flight self test for unmanned aerial vehicles (UAVs) | US14631137 | 2015-02-25 | US09540121B2 | 2017-01-10 | Charles Calvin Byers; Gonzalo Salgueiro |
| In one embodiment, a controller instructs an unmanned aerial vehicle (UAV) docked to a landing perch to perform a pre-flight test operation of a pre-flight test routine. The controller receives sensor data associated with the pre-flight test operation from one or more force sensors of the landing perch, in response to the UAV performing the pre-flight test operation. The controller determines whether the sensor data associated with the pre-flight test operation is within an acceptable range. The controller causes the UAV to launch from the landing perch based in part on a determination that UAV has passed the pre-flight test routine. | ||||||
| 176 | Unmanned aerial vehicle control method and unmanned aerial vehicle using same | US14793307 | 2015-07-07 | US09477229B1 | 2016-10-25 | Hou-Hsien Lee; Chang-Jung Lee; Chih-Ping Lo |
| A control method for an unmanned aerial vehicle (UAV) is provided. The UAV includes an accelerometer, a gyroscope, at least one drive unit and at least one rotor. The method includes: detecting current motion data from the accelerometer, wherein the motion data includes displacement of the UAV; determining whether the UAV is thrown up based on the motion data; detecting current ascending velocity of the UAV; determining whether the current ascending velocity of the UAV is substantially equal to zero; detecting current pitch angle and current angular velocity from the gyroscope if the current ascending velocity of the UAV is substantially equal to zero; calculating drive data based on the current pitch angle and current angular velocity; and enabling the at least one drive unit to drive at least one rotor to rotate so as to cause the UAV to hover evenly. | ||||||
| 177 | Unmanned aerial vehicle assistant | US14624504 | 2015-02-17 | US09471059B1 | 2016-10-18 | Steven James Wilkins |
| Techniques and systems for providing miniaturized unmanned aerial vehicles (UAVs) are disclosed. The techniques and systems can include significant off-board processing support for the UAVs to enable the UAVs to be smaller, lighter, and less expensive than conventional UAVs. The techniques and systems can include routines to provide enhanced support for police during routine traffic stops. The techniques and systems can also include routines to locate objects or people including, for example, locating a lost child in a crowd or a lost vehicle in a parking lot. The miniaturized UAVs can provide enhances perception for the user to enable the user to over and around objects for improved visibility and safety, among other things. | ||||||
| 178 | PROJECTILE LAUNCHED UAV RECONNAISSANCE SYSTEM AND METHOD | US14106733 | 2013-12-14 | US20160293015A1 | 2016-10-06 | Oleksiy Bragin |
| A method, system and computer readable medium for projectile launched UAV reconnaissance/surveillance are described. The method can include determining a designated target. The method can also include estimating a distance and trajectory from a launch point to the target and communicating distance and trajectory information to a launcher, a projectile and a communication and control system. The method can also include firing a separation charge when the UAV projectile reaches a predetermined point along the flight path, the separation charge being configured to separate a UAV from a projectile casing. The method can further include deploying the UAV and activating a propulsion system of the UAV and obtaining signals via one or more sensors. | ||||||
| 179 | UNMANNED AERIAL VEHICLE AND METHOD OF CONTROLLING THE SAME | US14845988 | 2015-09-04 | US20160272317A1 | 2016-09-22 | Taehoon CHO; Choonghwan SHIN |
| An unmanned aerial vehicle according to the present invention includes a housing mounted on a vehicle and having an inner space, the housing provided with a launching unit, an unmanned aerial vehicle accommodated in the housing and configured to be launched from the housing when a driving state of the vehicle meets a preset condition, wing units mounted to the unmanned aerial vehicle and configured to allow the flight of the unmanned aerial vehicle in response to the launch from the housing, an output unit disposed on the unmanned aerial vehicle, and a controller configured to control the wing units to move the unmanned aerial vehicle to a position set based on information related to the driving state when the unmanned aerial vehicle is launched, and control the output unit to output warning information related to the driving state. | ||||||
| 180 | Apparatus and method for launch and retrieval of a hovering aircraft | US14315899 | 2014-06-26 | US09434481B2 | 2016-09-06 | Brian T. McGeer |
| Various embodiments of the present disclosure provide an apparatus and method for launch and retrieval of a hovering aircraft. Generally, the apparatus of the present disclosure is configured to capture a hovering aircraft between two or more fingers of an aircraft capturer, guide the captured aircraft into a docking station for servicing and/or storage, and launch the aircraft from the docking station. The apparatus of the present disclosure is thus configured to bring the aircraft from an imprecise, irregular hover into a secure and well-controlled rest state. The tolerance of imprecision provided by the apparatus makes it particularly suited for use under a practical conditions such as aboard a small boat in a rough sea. | ||||||
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