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 |
|---|---|---|---|---|---|---|
| 101 | METHODS FOR LAUNCHING AND LANDING AN UNMANNED AERIAL VEHICLE | EP13828971 | 2013-12-13 | EP2906468A4 | 2016-06-29 | WANG MING-YU |
| 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. | ||||||
| 102 | METHODS FOR LAUNCHING AND LANDING AN UNMANNED AERIAL VEHICLE | EP13828971.5 | 2013-12-13 | EP2906468A1 | 2015-08-19 | WANG, Ming-yu |
| 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. | ||||||
| 103 | Short takeoff and landing aircraft | EP14187036.0 | 2014-09-30 | EP2889221A1 | 2015-07-01 | Ouellette, Rich P. |
A short takeoff and landing fixed wing aircraft (200) includes a primary powertrain (302) to provide power to a propulsion unit (208), a secondary powertrain (304) to provide power to the propulsion unit (208), and a detachable power coupling to transfer power to the secondary powertrain (304) from a source external to the fixed wing aircraft during takeoff.
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| 104 | UNMANNED AERIAL SYSTEMS | EP13845941.7 | 2013-07-25 | EP2879954A2 | 2015-06-10 | BYE, George; BICKEL, Matt |
| The present invention provides an Unmanned Aircraft System, including an integrated unmanned aerial vehicle and all related components and subsystems that can be packaged and transported as a kit, and customized to fit desired mission profiles, and easily repaired by replacement of damaged components or subsystems. The present invention further provides unmanned aircraft system components and subsystems that facilitate low power and low noise operation, and extended flight times. | ||||||
| 105 | SYSTEMS AND DEVICES FOR REMOTELY OPERATED UNMANNED AERIAL VEHICLE REPORT-SUPPRESSING LAUNCHER WITH PORTABLE RF TRANSPARENT LAUNCH TUBE | EP10833731 | 2010-09-09 | EP2475578A4 | 2015-04-01 | MIRALLES CARLOS THOMAS; SU GUAN H; ANDRYUKOV OLEKSANDR; MCNEIL JOHN |
| 106 | SURVEILLANCE SYSTEM | EP12818543.6 | 2012-12-05 | EP2800944A1 | 2014-11-12 | WARSOP, Clyde; PRESS, Andrew, Julian; DAVIES, Alan Geraint |
| 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 on 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. | ||||||
| 107 | Systems and methods to launch aircraft | EP13189774.6 | 2013-10-22 | EP2724941A1 | 2014-04-30 | Childress, Jamie J; Perron, Daniel J |
Systems and methods to launch an aircraft are disclosed. In one embodiment, a system to launch an aircraft comprises a launch arm comprising at least one load cell, an aircraft coupled to the launch arm, and a release mechanism in communication with the at least one load cell, wherein the release mechanism releases the aircraft when the at least one load cell indicates that a load on the launch arm is below a predetermined threshold. Other embodiments may be described.
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| 108 | Pre-flight self test for unmanned aerial vehicles (UAVs) | US15467463 | 2017-03-23 | US10131451B2 | 2018-11-20 | Gonzalo Salgueiro; Charles Calvin Byers |
| 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. | ||||||
| 109 | Vertically Oriented Tube-Launchable Rotary Wing Aircraft Having Respective Rotors at Opposite Ends of Main Body | US15941133 | 2018-03-30 | US20180281939A1 | 2018-10-04 | Steven K. Tayman |
| An expendable rotary wing unmanned aircraft capable of storage in a cylindrical housing includes a longitudinally extending body having an upper end and a lower end; and a pair of counter-rotating coaxial rotors each located at respective ends of longitudinally-extending body, wherein each rotor includes two or more blades, each blade rotatably coupled to a remainder of the rotor at a hinged joint and thereby extending along a length of the body in a storage configuration and extending radially outward from the body in a flight configuration. | ||||||
| 110 | MOBILE FULFILLMENT CENTERS WITH INTERMODAL CARRIERS AND UNMANNED AERIAL VEHICLES | US15460971 | 2017-03-16 | US20180265295A1 | 2018-09-20 | Brian C. Beckman; Nicholas Bjone |
| Intermodal vehicles may be loaded with items and an aerial vehicle, and directed to travel to areas where demand for the items is known or anticipated. The intermodal vehicles may be coupled to locomotives, container ships, road tractors or other vehicles, and equipped with systems for loading one or more items onto the aerial vehicle, and for launching or retrieving the aerial vehicle while the intermodal vehicles are in motion. The areas where the demand is known or anticipated may be identified on any basis, including but not limited to past histories of purchases or deliveries to such areas, or events that are scheduled to occur in such areas. Additionally, intermodal vehicles may be loaded with replacement parts and/or inspection equipment, and configured to conduct repairs, servicing operations or inspections on aerial vehicles within the intermodal vehicles, while the intermodal vehicles are in motion. | ||||||
| 111 | LAUNCHED AIR VEHICLE SYSTEM | US15913841 | 2018-03-06 | US20180257792A1 | 2018-09-13 | Thomas William Smoker |
| A launch canister for ejection from a submerged launch platform, the launch canister being adapted for ejection in a direction substantially along a first axis of the launch canister and comprising: an enclosure for carrying a UAV; a nose cap releasably located in a launch opening at a forward end of the launch canister; a launch mechanism for driving a UAV carried in the enclosure out of the launch canister through the launch opening in a direction substantially along said first axis; and a water surface sensor for detecting when the nose cap of the canister broaches the surface of the water; wherein the launch canister is configured to, on the water surface sensor detecting that the nose cap of the canister has broached the surface of the water, immediately release the nose cap and initiate the launch mechanism to drive a UAV carried in the enclosure out of the launch canister through the launch opening. | ||||||
| 112 | LAUNCHER FOR UNMANNED AERIAL VEHICLES | US15755699 | 2016-08-25 | US20180244402A1 | 2018-08-30 | MOSHE KAHLON; SHLOMO HAKIM |
| A launcher for unmanned aerial vehicles (UAV), the launcher having a foldable UAV stowed within said launcher, the launcher includes, a launch tube configured as a UAV launcher and a UAV carrying case. The launcher further includes a pneumatic booster connected to said UAV for accelerating said UAV during launching phase. The launcher further includes a separation mechanism operated to permits separation of the booster from the UAV when the UAV leaves the launcher tube and to transfer the kinetic energy that is created from the pneumatic booster to the UAV in the launching phase. The UAV is propelled off of the launch tube by the booster that transmits thrust in the launch tube to the space below said booster. The UAV which is connected to the booster by the separation mechanism is pushed out of the launcher tube body and leaves the launch tube, the booster is separated from the UAV by the separation mechanism and the UAV is automatically deployed. The UAV propellers are activated to propel the UAV and driven the UAV. | ||||||
| 113 | Unmanned aerial vehicle and method of controlling the same | US14845988 | 2015-09-04 | US10053217B2 | 2018-08-21 | 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. | ||||||
| 114 | TUBE LAUNCHED HYBRID MULTIROTOR METHODS AND APPARATUS FOR SYSTEM | US15380255 | 2016-12-15 | US20180170510A1 | 2018-06-21 | Keith M. Brock |
| A launching system may include a multirotor platform that includes a plurality of motors and propellers. The multirotor platform may be launched from a launch tube and actuated to transition from a storage state to a flight state where the propellers are operable via the motors. The multirotor platform may include pivotable pivoting motor arms that are connected between the main flight body and the propellers. After the multirotor platform is deployed from the launch tube, the pivoting motor arms may be actuated to extend from a retracted position against the main flight body and enable operation of the motors and the propellers for powered flight of the multirotor platform. The multirotor platform may include motor pylon wings connected to the motors and retractable nose gears for deploying the motor pylon wings and enabling unpowered flight or gliding movement of the multirotor platform. | ||||||
| 115 | UAV WITH SELECTIVE OPERATIONAL CONTROL DURING HOLDING | US15829690 | 2017-12-01 | US20180157276A1 | 2018-06-07 | Tobin Fisher; Johannes Becker Van Niekerk; Pavlo Manovi |
| A unmanned aerial vehicle (UAV) includes a body with plurality of motors, a motor controlling circuit, a microprocessor for controlling the flight state of the UAV, a plurality of motion sensors, and a capacitive touch sensor incorporated into a battery. When the user grasps the UAV by the battery, the touch sensor is activated and the microprocessor alters the flight state of the UAV. | ||||||
| 116 | NON- MOTORIZED TYPE FLYING UNIT FOR OBSERVATION | US15793342 | 2017-10-25 | US20180111682A1 | 2018-04-26 | Seung Bum KIM |
| A non-motorized flying unit for observation according to an exemplary embodiment of the present disclosure includes: a body part which is mounted on a launcher, launched in a direction toward a preset target when the launcher operates, and falls, by its own weight, toward the ground from a position of a top dead point (TDP); a propeller unit which is coupled to the body part, and automatically generates rotational force by means of drag force applied to the body part when the body part falls so as to decrease a falling velocity of the body part; and an image capturing unit which is installed on the body part, and obtains image information in respect to the ground when the body part falls. | ||||||
| 117 | Modularized armor structure with unmanned aerial vehicle loaded and armored vehicle using the same | US14668020 | 2015-03-25 | US09952022B2 | 2018-04-24 | Yoshihiko Ueno; Shojiro Furuya |
| An armored vehicle includes: a basic armored vehicle having a predetermined basic external armor; a modularized armor structure exchangeably attached to the basic external armor; and an unmanned aerial vehicle loaded on the modularized armor structure. The modularized armor structure includes: an unmanned aerial vehicle loading section configured to load the unmanned aerial vehicle; an armoring material structure formed of armoring material; and an attaching section used to exchangeably attach the modularized armor structure to the basic armored vehicle. | ||||||
| 118 | Unmanned Aerial Vehicle Systems and Methods of Use | US15844207 | 2017-12-15 | US20180101169A1 | 2018-04-12 | Paul G. Applewhite |
| An improved unmanned aerial vehicular system having a rotor head assembly with any balanced number of rotary wings or blades, a generally tubular body assembly, a gimballed neck connecting the head to the body, and a navigation, communications and control unit such as for military and humanitarian operations, including payload delivery and pickup. The vehicle is generally guided using a global positioning satellite signal, and by pre-programmed or real time targeting. The vehicle is generally electrically powered and may be launched by one of (a) hand-launch, (b) air-drop, (c) catapult, (d) tube-launch, or (e) sea launch, and is capable of landing on both static and dynamic targets. Once launched, unmanned aerial vehicles may be formed into arrays on a target area and find use in surveillance, warfare, and in search-and-rescue operations. | ||||||
| 119 | CAPTURE AND LAUNCH APPARATUS AND METHOD OF USING SAME FOR AUTOMATED LAUNCH, RETRIEVAL, AND SERVICING OF A HOVERING AIRCRAFT | US15421732 | 2017-02-01 | US20180050823A1 | 2018-02-22 | Brian T. McGeer |
| Automated launch and retrieval of a “tail-sitting” VTOL aircraft is accomplished by exploiting the natural stability of hover when restrained in tension by an upwind wing tip. For retrieval, a flexible rod is lifted into contact with the trailing edge of the upwind wing as the aircraft translates downwind overhead. Sliding between the rod and wing leads to interlocking of hooks at the rod end and wing tip, while the aircraft swings into a stable tethered hover downwind of the rod. The rod is then used to pull the aircraft upwind into a fixture for secure parking and servicing. After servicing, the aircraft lifts-off into tethered hover, and power margin for climb is assessed. If the aircraft is judged to have sufficient power safely to proceed, then the interlocking hooks are disengaged, leaving the aircraft to climb away in free flight. | ||||||
| 120 | Stitched image | US13547352 | 2012-07-12 | US09870504B1 | 2018-01-16 | 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. | ||||||
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