| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 244170230 | Having plural lifting rotors | 75 |
| 20090008499 | Modular flying vehicle - The invention is a modular vehicle having an air vehicle that can be coupled to cargo containers, land vehicles, sea vehicles, medical transport modules, etc. In one embodiment the air vehicle has a plurality of propellers positioned around a main airframe, which can provide vertical thrust and/or horizontal thrust. One or more of the propellers may be configured to tilt forward, backward, and/or side-to-side with respect to the airframe. | 01-08-2009 |
| 20090127380 | DUAL POWER HELICOPTER WITHOUT A TAIL ROTOR - A dual power helicopter without a tail rotor is especially a kind of helicopter with an enhanced ascending and descending power through the dual power. The dual power helicopter of present invention primarily uses two power devices which can be rotated in opposite directions to control a flight of the helicopter. The two power devices are rotated in the opposite directions by steering gears from a same engine, such that the engine power can be completely transmitted to the two power device, enabling the engine power to be completely developed, thereby improving a performance of the helicopter. | 05-21-2009 |
| 20090127381 | System, method and apparatus for aircraft having counter-rotating, ring-winged rotors - An aircraft having counter-rotating, ring-type wing rotors that are driven by engines located at the wing tips is disclosed. The aircraft incorporates large span, high aspect ratio wings that are configured in a joined-tip design to improve the structural characteristics of the wings. One of the wings counter-rotates inside the other wing to enable vertical take-off and landing. The wings may comprise elliptical shapes, each having upper and lower sections that are separated from each other. | 05-21-2009 |
| 20090134269 | Power Assembly and a Coaxial Twin Propeller Model Helicopter Using the Same - The present invention provides a power assembly which is used for driving a twin propeller rotation assembly and a tail rotation assembly of said coaxial twin propeller model helicopter at the same time, said twin propeller rotation assembly composed of a main rotation assembly and a minor rotation assembly, said power assembly comprises a motor assembly and a gear assembly, said motor assembly comprises a motor, a motor gear, and a fuel tank, said motor connected to said motor gear, said fuel tank provided fuel to said motor, said motor driving said motor gear, said gear assembly comprises a main gear, a synchronous belt gear and a belt pulley, said main gear engaged said motor gear, said main gear connected to said main rotation assembly, a lower part of said main gear connected to said synchronous belt gear, said synchronous belt gear connected to said minor rotation assembly, an upper end of said belt pulley connected to said tail rotation assembly, a middle part of said belt pulley engaged said main gear, a lower end of said belt pulley connected to said synchronous belt gear. The power assembly has simple structure, easy assembly, and stable flight, meanwhile, said power assembly drive a twin propeller rotation assembly and a tail rotation assembly synchronously with one motor. The present invention further provide a coaxial twin propeller model helicopter with the power assembly. | 05-28-2009 |
| 20090145997 | INTEGRAL POWERED WING AIRCRAFT - Disclosed is a rotary winged aircraft. More specifically, this invention relates to an aircraft wherein lift is generated by two discs which rotate about a central axis. The discs generate equal and opposite forces such that the central axis remains fixed, thereby allowing it to be used for a crew compartment. In one embodiment, the two discs are concentrically located. | 06-11-2009 |
| 20090145998 | AIRCRAFT USING TURBO-ELECTRIC HYBRID PROPULSION SYSTEM - An air vehicle incorporating a hybrid propulsion system. The system includes a gas turbine engine as a first motive power source, and one or more battery packs as a second motive power source. Through selective coupling to a DC electric motor that can in turn be connected to a bladed rotor or other lift-producing device, the motive sources provide differing ways in which an aircraft can operate. In one example, the gas turbine engine can provide operation for a majority of the flight envelope of the aircraft, while the battery packs can provide operation during such times when gas turbine-based motive power is unavailable or particularly disadvantageous. In another example, both sources of motive power may be decoupled from the bladed rotor such that the vehicle can operate as an autogyro. | 06-11-2009 |
| 20090230235 | Tambourine helicopter - Disclosed is a profile of an end view of a base portion Vertical Take Off And Landing Craft, (VTLC) rotor-blade comprising a widened structure from leading to trailing edges. The profile further comprises straight level planes of air foil that provide the options of transforming the leading edge to the trailing edge. The rotor wing system is housed and duplicated in the craft set within said two wells which are circumnavigated by a corridor from front to aft of the craft. Two rear exits are reinforced by the connection of a triangular structure forming a tail which also affords a comprehensive view of the complete air craft perimeter from the viewpoint of a central top compartment. | 09-17-2009 |
| 20090283629 | HOVERING AERIAL VEHICLE WITH REMOVABLE ROTOR ARM ASSEMBLIES - The invention provides a hovering aerial vehicle with removable rotor arms and protective shrouds. Removing the shrouds reduces the weight of the vehicle and increases flight time. Removing the rotor arms makes the vehicle easier to transport. Removable rotor arms also simplify field repair or replacement of damaged parts. | 11-19-2009 |
| 20100012769 | AERODYNAMIC INTEGRATION OF A PAYLOAD CONTAINER WITH A VERTICAL TAKE-OFF AND LANDING AIRCRAFT - A vertical takeoff and landing (VTOL) rotary-wing air-craft is sized and configured to match a payload container such as a standardized Joint Modular Intermodal Container (JMIC). The aircraft may be an Unmanned Air Vehicle (UAV) that is capable of autonomously engaging and disengaging the container so that the aircraft can pick up and drop off the JMIC with minimum human intervention. | 01-21-2010 |
| 20100025526 | Dual Rotor Vertical Takeoff and Landing Rotorcraft - A rotorcraft having two coaxial, counter-rotating rotors, one proximate to the forward end of the fuselage and one proximate to the aft end of the fuselage, that generate the forces necessary to lift the craft and maneuver it in the air by adjusting the pitch of the rotor blades throughout their rotation, and a method of flying a dual rotor rotorcraft involving taking off in a vertical orientation, climbing vertically, transitioning to generally horizontal flight, flying horizontally, and subsequently repeating the sequence in reverse to land again in a vertical orientation. | 02-04-2010 |
| 20100044499 | Six rotor helicopter - A rotary wing aircraft is provided having at least three rotor pairs. Each rotor pair has an upper rotor and a lower rotor. During operation, the upper rotor and lower rotor rotate around a shared rotor axis with the upper rotor rotating in a first direction and the lower rotor rotating in an opposite direction By independently controlling the speed of rotation of each upper rotor and each lower rotor the aircraft can be made to ascend, descend, move forward, move backward, move side to side, yaw right and yaw left by only varying the relative speeds of rotations of the upper rotors and lower rotors. | 02-25-2010 |
| 20100108801 | Dual rotor helicopter with tilted rotational axes - A rotary wing aircraft apparatus includes a body and a rotor pair connected to the body by an arm. The rotor pair has an upper rotor driven by an upper motor and rotating about an upper rotor axis and a lower rotor driven by a lower motor and rotating about a lower rotor axis. The upper and lower rotor axes are tilted with respect to each other. Tilting the axes away from the arm increases the distance from the rotor blades to the arm, and decreases the risk of the blades of the rotor contacting the arm. In an aircraft with a plurality of arms extending from the body, and a rotor assembly connected to each arm, the arms can be pivoted from a flying position, where the arms extend laterally outward to a folded position where the arms are positioned substantially parallel and adjacent to each other. | 05-06-2010 |
| 20100243793 | FLYING APPARATUS - Flying apparatus includes a housing and rotary means associated with said housing capable of rotation in use. The rotary means includes two or more rotary blades. Each rotary blade has weighted means associated with at least a part of a leading edge thereof. | 09-30-2010 |
| 20100243794 | FLYING APPARATUS - Flying apparatus is provided including a housing with two or more rotor means associated therewith. The rotor means are arranged to rotate about substantially parallel axes in use. One or more vanes are provided with said apparatus to help stabilize the apparatus in use. | 09-30-2010 |
| 20100264256 | COUNTER-ROTATIONAL INERTIAL CONTROL OF ROTORCRAFT - A rotorcraft with two counter-rotating rotors and method for inertially controlling the rotorcraft. The rotorcraft includes a hinged frame configured such that at least one inter-rotor angle of the two counter-rotating rotors is controlled by at least one actuated hinge of the hinged frame and the rotational axes of the two counter-rotating rotors are substantially collinear when the actuated hinge is in a fully open position. The sum of the magnitudes of torque applied to the two counter-rotating rotors is varied to control the lift of the rotorcraft. The difference of the magnitudes of torque applied to the two counter-rotating rotors is varied to control the yaw of the rotorcraft. The at least one inter-rotor angle is varied using the at least one actuated hinge to control the pitch and/or roll of the rotorcraft. | 10-21-2010 |
| 20110017865 | Rotary-Wing Aircraft - The invention relates to a rotary-wing aircraft ( | 01-27-2011 |
| 20110024554 | TWIN ROTOR FLYING VEHICLE - A flying vehicle is provided that comprises first and second rotors respectively mounted in rotation about first and second rotation axes, the first rotor including a first group of blades extending in a first blade plane and the second rotor including a second group of blades extending in a second blade plane, each of the first and second rotors being rotated by a driving means of the machine. The driving means includes at least one engine arranged between said rotors and between said first and second blade planes. | 02-03-2011 |
| 20110226892 | ROTARY WING VEHICLE - Embodiments of the invention relate to a vehicle comprising a plurality of inclined rotors that are operable to provide at least one of thrust and torque vectoring according to a desired thrust and/or torque vectors. | 09-22-2011 |
| 20110315810 | Airborne, tethered, remotely stabilized surveillance platform - An airborne surveillance platform supporting optoelectronic and electronic sensors, including level sensors, is automatically stabilized in a horizontal plane by varying the length of two tethers out of three. Error signals from the level sensors are transmitted over a wireless link to control components on a rotating platform on the host vehicle, which automatically vary the length of tethers. Applications include images of the surrounding terrain generated by a video camera and a thermal imager in military, police and civil emergency operations. | 12-29-2011 |
| 20120138732 | Helicopter with folding rotor arms - A rotary wing aircraft apparatus includes a body and a rotor pair connected to the body by an arm. The rotor pair has an upper rotor driven by an upper motor and rotating about an upper rotor axis and a lower rotor driven by a lower motor and rotating about a lower rotor axis. The upper and lower rotor axes are tilted with respect to each other. Tilting the axes away from the arm increases the distance from the rotor blades to the arm, and decreases the risk of the blades of the rotor contacting the arm. In an aircraft with a plurality of arms extending from the body, and a rotor assembly connected to each arm, the arms can be pivoted from a flying position, where the arms extend laterally outward to a folded position where the arms are positioned substantially parallel and adjacent to each other. | 06-07-2012 |
| 20120168556 | PRE-LANDING, ROTOR-SPIN-UP APPARATUS AND METHOD - A method and apparatus for reducing roll of rotorcraft landing in autorotation may include executing a flight with a rotorcraft. The flight may include first, second, and third portions ordered sequentially. During the first portion, the rotorcraft may be flown with the rotor exclusively in autorotation. During the second portion, the rotorcraft may be flown with the rotor powered at least partially by an engine of the rotorcraft, which may increase the rotational speed of the rotor. During the third portion, the rotorcraft may be flown with the rotor exclusively in autorotation. The flight and the third portion may terminate simultaneously with a touch down of the rotorcraft. Kinetic energy stored in the rotor during the second portion, during the third portion, bring the ground speed of the rotorcraft to substantially zero before touching down. | 07-05-2012 |
| 20120298793 | FLYING ELECTRIC GENERATORS WITH CLEAN AIR ROTORS - Flying electric generator aircraft that include groupings of four rotors mounted to booms extending fore and aft of a fuselage structure wherein the rotors are placed so that when the aircraft is facing the wind, each rotor has a direct path to an undisturbed flow of air, regardless of pitch angle and during all flight maneuvers of the aircraft. The rotors are placed in counter-rotating pairs with the booms preferably angled so that the rotors in the front of the aircraft are spaced at a distance from one another that is different than a spacing of the rotors at the rear of the aircraft. | 11-29-2012 |
| 20130068878 | Self-Healing Reservoir Coating System - The system includes a coating for a reservoir, the coating being configured to self-heal following a penetration by a projectile through the coating and the reservoir. The coating is an elastomeric polymer coating having sufficient elasticity to so as return to the coating to an approximate original shape after the projectile has passed through the coating. Further, the coating is configured to hold the reservoir together following severe damage from the projectile. | 03-21-2013 |
| 20130334362 | PLANETARY DE-ROTATION SYSTEM FOR A SHAFT FAIRING SYSTEM - A fairing system according to an exemplary aspect of the present disclosure includes, among other things, a shaft fairing mounted for rotation about an axis of rotation and a planetary gear set configured to control a position of the shaft fairing about the axis of rotation. | 12-19-2013 |
| 20140014767 | Self-Righting Frame And Aeronautical Vehicle - An aeronautical vehicle that rights itself from an inverted state to an upright state has a self-righting frame assembly has an apex preferably at a top of a central vertical axis. The apex provides initial instability to begin a self-righting process when the vehicle is inverted on a surface. A lift and stabilization panel extends across an upper portion of said frame to provide lift, drag and/or stability. A propulsion system can be located within a central void of the frame assembly and oriented to provide a lifting force. An electronics assembly is also carried by the self-righting frame for receiving remote control commands and is communicatively interconnected to the power supply for remotely controlling the aeronautical vehicle to take off, to fly, and to land on a supporting surface. The frame provides self-righting functionality and protection of elements carried therein. | 01-16-2014 |
| 20140091172 | ROTARY WING VEHICLE - A rotary wing vehicle includes a body structure having an elongated tubular backbone or core, and a counter-rotating coaxial rotor system having rotors with each rotor having a separate motor to drive the rotors about a common rotor axis of rotation. The rotor system is used to move the rotary wing vehicle in directional flight. | 04-03-2014 |
| 20140117149 | Tetra-Propeller Aircraft - Described herein is a vertical take-off and landing aircraft comprising: an upper enclosure comprising a first upper arm and a second upper arm; a lower enclosure comprising a first lower arm and a second lower arm; wherein the first upper arm and the first lower arm comprise a first upper buckle and a first lower buckle, respectively; wherein the second upper arm and the second lower arm comprise a second upper buckle and a second lower buckle, respectively; wherein the first upper buckle engages the first lower buckle and the second upper buckle engages the second lower buckle, thereby securing the upper enclosure to the lower enclosure. | 05-01-2014 |
| 20140131510 | UNMANNED AERIAL VEHICLE AND OPERATIONS THEREOF - The present invention provides methods and apparatus for unmanned aerial vehicles (UAVs) with improved reliability. According to one aspect of the invention, interference experienced by onboard sensors from onboard electrical components is reduced. According to another aspect of the invention, user-configuration or assembly of electrical components is minimized to reduce user errors. | 05-15-2014 |
| 20140138477 | INVERTIBLE AIRCRAFT - A rotorcraft including a fuselage, one or more motor-driven rotors for vertical flight, and a control system. The motors drive the one or more rotors in either of two directions of rotation to provide for flight in either an upright or an inverted orientation. An orientation sensor is used to control the primary direction of thrust, and operational instructions and gathered information are automatically adapted based on the orientation of the fuselage with respect to gravity. The rotors are configured with blades that invert to conform to the direction of rotation. | 05-22-2014 |
| 20140151496 | Modular Flying Vehicle - The invention is a modular vehicle having an air vehicle that can be coupled to cargo containers, land vehicles, sea vehicles, medical transport modules, etc. In one embodiment the air vehicle has a plurality of propellers positioned around a main airframe, which can provide vertical thrust and/or horizontal thrust. One or more of the propellers may be configured to tilt forward, backward, and/or side-to-side with respect to the airframe. | 06-05-2014 |
| 20140175214 | VTOL_TWIN_PROPELLER_ATTITUDE_CONTROL_AIR_VEHICLE - A commonly assumed operational requirement for a multi-rotor vehicle, often referred to as a “Quad-Copter” or “Quad-Rotor”, is to have onboard a minimum of three motors, in order to provide a stable hover, and more frequently as many as eight motors. The Twin Propeller Attitude Control (TPAC) Air Vehicle, using a hybrid stabilization system, needs only two motors, in order to achieve full control of altitude, pitch, roll and yaw. Pitch control is achieved by means of differential thrust, while roll and yaw control is accomplished via thrust vectoring. In the event of loss power of one or both engines, a parachute will be automatically released. | 06-26-2014 |
| 20140263822 | VERTICAL TAKE OFF AND LANDING AUTONOMOUS/SEMIAUTONOMOUS/REMOTE CONTROLLED AERIAL AGRICULTURAL SENSOR PLATFORM - The invention provides for a vertical takeoff and landing capable aerial vehicle with multiple rotors that is designed to carry agricultural sensors and telemetry allowing for real time control of agricultural equipment in accord with sensor data. The ability to carry a suite of agricultural sensors combined with multiple rotors will allow the craft to operate quickly in hovering and longitudinal flight over rows of farm fields and other vegetation and use an NDVI imager and other sensors to take data readings and real time imagery which will allow farmers and other personnel to determine vegetation type, need for chemical applications, plant fertilization, irrigation requirements, and other vegetation features including types of vegetation present. This will allow for precision agricultural, vegetation, and crop management and for farmers it will increase the efficiency of precision agriculture operations. | 09-18-2014 |
| 20140263823 | TRANSFORMABLE AERIAL VEHICLE - Systems, devices, and methods for a transformable aerial vehicle are provided. In one aspect, a transformable aerial vehicle includes: a central body and at least two transformable frames assemblies respectively disposed on the central body, each of the at least two transformable frame assemblies having a proximal portion pivotally coupled to the central body and a distal portion; an actuation assembly mounted on the central body and configured to pivot the at least two frame assemblies to a plurality of different vertical angles relative to the central body; and a plurality of propulsion units mounted on the at least two transformable frame assemblies and operable to move the transformable aerial vehicle. | 09-18-2014 |
| 20140299708 | ROCKET OR BALLISTIC LAUNCH ROTARY WING VEHICLE - Embodiments of the present invention relate to a rocket or ballistic launch rotary wing air vehicle. | 10-09-2014 |
| 20140339355 | COMPACT UNMANNED ROTARY AIRCRAFT - A rotary wing aircraft apparatus has arms extending from a body, and a rotor assembly attached to an end of each arm. Each rotor assembly has a rotor blade releasably attached by a lock mechanism. A clockwise rotor blade is releasably attached to a first rotor assembly by engagement in a clockwise lock mechanism, and a counterclockwise rotor blade is releasably attached to a second rotor assembly by engagement in a counterclockwise lock mechanism. The clockwise rotor blade is engageable only with the clockwise lock mechanism and the counterclockwise rotor blade is engageable only with the counterclockwise lock mechanism and cannot be engaged in the clockwise lock mechanism. A leg extends down from each rotor assembly to support the apparatus on the ground. | 11-20-2014 |
| 20140374535 | AERIAL DISPLAY SYSTEM WITH FLOATING PIXELS - A system for performing an aerial display. The system includes a plurality of UAVs each including a propulsion device and a display payload, and the system includes a ground station system with a processor executing a fleet manager module and memory storing a different flight plan and a set of display controls for the UAVs. Then, wherein, during a display time period, the UAVs concurrently execute the flight plans through operation of the propulsion devices and operate the display payloads based on the display controls. The display payloads each include a lighting assembly and a light controller. The output light is one of a two or more colored light streams, and each of the display payloads further may include a light diffuser with the output light being directed onto a surface of the light diffuser. The light diffuser may include a light diffusing screen extending about the lighting assembly. | 12-25-2014 |
| 20150021429 | Remote-Controlled Aerial Device Platform - The invention relates to an aircraft ( | 01-22-2015 |
| 20150060596 | TORQUE SPLIT GEARBOX FOR ROTARY WING AIRCRAFT - A gearbox system for a dual coaxial counter rotating rotor assembly includes an input shaft to input a first torque into the gearbox system and a transfer shaft operably connected to the input shaft to transfer the first torque therethrough. Two gear sets are operably connected to the transfer shaft. Each gear set includes a first output gear to transfer a second torque acting in a first direction to a first rotor of a rotor assembly and a second output gear to transfer the second torque acting in a second direction opposite the first direction to a second rotor of the rotor assembly. The second torque transferred by each gear set of the two gear sets is substantially equal. | 03-05-2015 |
| 20150102159 | WATERPROOF MULTI-ROTOR UNMANNED FLYING APPARATUS - Disclosed is an invention related to a waterproof unmanned flying apparatus, which is waterproof or water resistant and can perform in inclement weather conditions. The flying apparatus comprises of a main frame covering the outer structure of the flying apparatus that is constructed out of a single piece or multiple pieces which are fused together or mechanically attached to create a watertight seal. A centralized frame can be configured in numerous layouts to include the size and number of rotor blades. The flying apparatus can be used in various applications such as a training device, an aerial photography, and any other event for which the flying apparatus would be required to fly in or around water. The flying apparatus protects expensive internal electrical components that would normally be destroyed by water and moisture. Furthermore, the flying apparatus can be attached with devices for providing features intended for user's consumption. | 04-16-2015 |
| 20150122941 | COUNTER-ROTATING ROTOR SYSTEM WITH FAIRING - A coaxial, dual rotor system for an aircraft includes a first rotor assembly located at a rotor axis and a second rotor assembly located at the rotor axis. An aerodynamic fairing is positioned between the first rotor assembly and the second rotor assembly along the rotor axis. A planetary gear arrangement is operably connected to the fairing and operably connected to an airframe of the aircraft to maintain a selected rotational orientation of the fairing about the rotor axis relative to the airframe. | 05-07-2015 |
| 20150129711 | ROTARY-WING DRONE WITH GEARLESS-DRIVE AND FAST-MOUNTING PROPELLERS - Each propulsion unit of the drone comprises a propeller ( | 05-14-2015 |
| 20150321754 | Coaxial Counter-Rotating Unmanned Helicopter - To configure the yaw axis control mechanism of a coaxial counter-rotating unmanned helicopter to be able to accurately control the pitch angle of the upper rotor blade by a simple configuration even if the precise adjustment is not performed. A rudder control rod is inserted into a main mast of a coaxial counter-rotating helicopter, a lower end portion thereof is connected to an output lever of the rudder servo, and a mixing rod head is fixed to an upper end portion. A link mechanism connected to the upper swash plate is attached to a side surface portion of the mixing rod head, the vertical displacement of the mixing rod head moving up and down together with the rudder control rod is converted into a displacement for tilting an upper blade holder around the spindle via the link mechanism, thereby changing the pitch angle of the upper rotor blades. | 11-12-2015 |
| 20150321755 | COLLAPSIBLE MULTI-ROTOR UAV - A multi-rotor UAV having a pull pin mechanism that engages and disengages the rotor arms from a deployed, in-flight position to a storage or transport configuration, thus making the UAV more portable and capable of carrying larger payloads with the flexibility of folding into a smaller configuration or profile for transport, such as in a backpack. The device includes a rotor arm utilization of a pull pin mechanism to lock and unlock the position of the arms, and a proprietary frame. | 11-12-2015 |
| 20150321759 | ROTARY-WING DRONE OF THE QUADRICOPTER TYPE, PROVIDED WITH REMOVABLE BUMPERS FOR PROTECTING THE PROPELLERS - The drone ( | 11-12-2015 |
| 20150353192 | ALL-ELECTRIC MULTIROTOR FULL-SCALE AIRCRAFT FOR COMMUTING, PERSONAL TRANSPORTATION, AND SECURITY/SURVEILLANCE - Methods and systems for a full-scale vertical takeoff and landing manned or unmanned electric aircraft, having an all-electric, non-hydrocarbon-powered lift and propulsion system, an integrated avionics system for navigation and guidance, and simple joystick and throttle controls to provide the operator with ‘drive by wire’ style direction control. The vehicle employs counter-rotating sets of propellers and lift is provided by multiple pairs of small electric motors driving directly-connected, counter-rotating sets of propellers. Automatic computer monitoring by one or a plurality of programmed redundant digital motor management computer or autopilot controls each motor-controller and motor to produce pitch, bank and elevation, while simultaneously restricting the flight regime that the pilot can command. Sensed multi-axis information and parameter values about vehicle state are used to provide stable vehicle control and to detect when stable vehicle operating limits are about to be exceeded. | 12-10-2015 |
| 20160001875 | VERTICAL TAKE-OFF AND LANDING AERIAL VEHICLE - A VTOL (vertical take-off and landing) aerial flying vehicle comprising an inner frame, a gimbal system and an outer frame, the inner frame comprising a propulsion system and a control system. The propulsion system being able to generate a lift force. The VTOL may also include a decoupling mechanism having either a linear or non-linear beam coupled to a ring. The beam may optionally include sliders at ends thereof that provide an additional rotation freedom to the inner frame. | 01-07-2016 |
| 20160001883 | UNMANNED AERIAL VEHICLE LANDING INTERFACE - The present disclosure is directed toward systems and methods for autonomously landing an unmanned aerial vehicle (UAV). In particular, systems and methods described herein enable a UAV to land within and interface with a UAV ground station (UAVGS). In particular, one or more embodiments described herein include systems and methods that enable a UAV to conveniently interface with and land within a UAV ground station (UAVGS). For example, one or more embodiments include a UAV that includes a landing base and landing frame that interfaces with a landing housing of a UAVGS. | 01-07-2016 |
| 20160023744 | TRANSFORMABLE AERIAL VEHICLE - Systems, devices, and methods for a transformable aerial vehicle are provided. In one aspect, a transformable aerial vehicle includes: a central body and at least two transformable frames assemblies respectively disposed on the central body, each of the at least two transformable frame assemblies having a proximal portion pivotally coupled to the central body and a distal portion; an actuation assembly mounted on the central body and configured to pivot the at least two frame assemblies to a plurality of different vertical angles relative to the central body; and a plurality of propulsion units mounted on the at least two transformable frame assemblies and operable to move the transformable aerial vehicle. | 01-28-2016 |
| 20160023759 | MOVABLE MEMBER BEARING AERIAL VEHICLES AND METHODS OF USE - An aerial vehicle includes a body having a longitudinal axis, a plurality of movable members emanating connected to the body, at least one motor, and at least three aerodynamic propulsors driven by the at least one motor. The movable members are connected to the body and extend away from the body. | 01-28-2016 |
| 20160032895 | FLYING ELECTRIC GENERATORS WITH CLEAN AIR ROTORS - Flying electric generator aircraft that include groupings of four rotors mounted to booms extending fore and aft of a fuselage structure wherein the rotors are placed so that when the aircraft is facing the wind, each rotor has a direct path to an undisturbed flow of air, regardless of pitch angle and during all flight maneuvers of the aircraft. The rotors are placed in counter-rotating pairs with the booms preferably angled so that the rotors in the front of the aircraft are spaced at a distance from one another that is different than a spacing of the rotors at the rear of the aircraft. | 02-04-2016 |
| 20160083084 | UNMANNED AERIAL VEHICLE AND OPERATIONS THEREOF - The present invention provides methods and apparatus for unmanned aerial vehicles (UAVs) with improved reliability. According to one aspect of the invention, interference experienced by onboard sensors from onboard electrical components is reduced. According to another aspect of the invention, user-configuration or assembly of electrical components is minimized to reduce user errors. | 03-24-2016 |
| 20160096614 | AERIAL VEHICLE WITH FRAME ASSEMBLIES - Systems, devices, and methods for a transformable aerial vehicle are provided. In one aspect, a transformable aerial vehicle includes: a central body and at least two transformable frames assemblies respectively disposed on the central body, each of the at least two transformable frame assemblies having a proximal portion pivotally coupled to the central body and a distal portion; an actuation assembly mounted on the central body and configured to pivot the at least two frame assemblies to a plurality of different vertical angles relative to the central body; and a plurality of propulsion units mounted on the at least two transformable frame assemblies and operable to move the transformable aerial vehicle. | 04-07-2016 |
| 20160101850 | Multi-rotor frame structure - This invention relates to a multi-rotor aircraft frame structure, which is mainly the use of stainless steel tubes and engineering plastics has the rigidity and toughness, directly to the stainless steel tubes symmetrical inserted nailed in plastic sheet to constitute the main frame structure, and by connecting plurality support blocks and plurality support rods to construct a kind of peripheral support structure to obtain sufficient structural strength, thereby to constructing a light weight and low cost and practicality high-performance multi-rotor aircraft frame. | 04-14-2016 |
| 20160122010 | AERIAL VEHICLE - An aerial vehicle includes a body, a plurality of rotors coupled to the body and configured to provide lift, a plurality of driving devices coupled to the rotors respectively and configured to drive the rotors to rotate, and a control device coupled to the body and the driving devices. The control device includes a gyroscope and a controller. The gyroscope is configured to collect information of rotation speed of the body and transmit the information of the rotation speed to the controller. The controller is configured to provide a driving power for adjusting the rotation speed of the body according the information of the rotation speed, and produce and transmit a control signal of the driving power to the driving devices to output the driving power to corresponding rotors to adjust the rotation speed of the body. | 05-05-2016 |
| 20160122012 | DRONE - There is disclosed a drone including a main body comprising a motor, a shaft inserted in the main body vertically, a wing unit rotatable on the shaft by a power generated from the motor, the wing unit comprising a propeller unfolded horizontally and folded vertically, wherein the motor comprises a first motor and a second motor, and the shaft comprises an upper shaft inserted in the main body from a top vertically and a lower shaft inserted in the main body from a bottom vertically, and the wing unit comprises a first wing unit rotated on the upper shaft in a first direction by a power generated from the first motor, and a second wing unit rotated on the lower shaft in a second direction, which is the reverse of the first direction, by a power generated from the second motor. | 05-05-2016 |
| 20160122015 | UNMANNED AERIAL VEHICLE - Unmanned aerial vehicles and methods for providing the same are disclosed. The unmanned aerial vehicles may have various configurations related to a support frame. The unmanned aerial vehicles may have various configurations with a continuous track for ground propulsion. The unmanned aerial vehicles may have various configurations related to payload clamps. | 05-05-2016 |
| 20160122016 | FOLDABLE AND SELF-DEPLOYABLE AERIAL VEHICLE - An aerial vehicle including self-autonomous deployable arms and methods of deploying the vehicle are disclosed. The arms may include patterns located thereon that allow the arms to transition between wrapped, flat, and deployed configurations autonomously without the need for direct intervention by a user. | 05-05-2016 |
| 20160122017 | Structure and Manufacturing Process for Unmanned Aerial Vehicle - The application discloses an unmanned aerial vehicle (UAV) device and the manufacturing process to make the UAV. The UAV device comprises a monocoque shell with a single-piece molded construction that includes a central body and arms that extend outward from the central body. Each of the arms includes a terminal end that is spaced away from the central body. The monocoque shell has a cupped shape with a closed first side and an open second side that includes sidewalls that extend around an interior space. The UAV device comprises a plurality of motors and rotors attached to the first side of the monocoque shell with one of said plurality of motors and rotors positioned at the terminal end of each of the arms. | 05-05-2016 |
| 20160137298 | Multi-Rotor Aircraft - Disclosed is a multi-rotor aircraft having a hollow center boom from which extends three or more leg booms disposed generally perpendicular to the center boom and on which is mounted rotor bases that have rotor rotation means and rotor blades. In another aspect the invention is programmed means for control of the craft described above and methods of control of the craft in flight. | 05-19-2016 |
| 20160137304 | MICRO HYBRID GENERATOR SYSTEM DRONE - An unmanned aerial vehicle comprising at least one rotor motor. The rotor motor is powered by a micro hybrid generation system. The micro hybrid generator system comprises a rechargeable battery configured to provide power to the at least one rotor motor, a small engine configured to generate mechanical power, a generator motor coupled to the small engine and configured to generate AC power using the mechanical power generated by the small engine, a bridge rectifier configured to convert the AC power generated by the generator motor to DC power and provide the DC power to either or both the rechargeable battery and the at least one rotor motor, and an electronic control unit configured to control a throttle of the small engine based, at least in part, on a power demand of at least one load, the at least one load including the at least one rotor motor. | 05-19-2016 |
| 20160137312 | UNMANNED AERIAL VEHICLE LAUNCH SYSTEM - Aspects of the present invention relate to unmanned aerial vehicle launch technologies. | 05-19-2016 |
| 20160144953 | REMOTE-CONTROLLED PLATFORM SHAPED AIRCRAFT - The subject matter of the invention is a remote-controllable, disk-shaped aircraft platform, comprising a platform housing and at least one transport housing, the platform housing having a plurality of motor-driven, horizontally aligned rotors, each rotor being connected via a support arm to a support structure holding the support arms of the rotors, the support structure being centrally arranged in the platform housing, the support structure accommodating at least one transport housing in a vibrationally isolated manner. | 05-26-2016 |
| 20160144954 | UNMANNED AERIAL VEHICLE - Herein is disclosed an unmanned aerial vehicle having motor arm holders configured such that when inserted into its corresponding arm holder on the central hub or holder, the motor arm holders are tilted at an angle between 6 to 10 degrees angle upwards. This drops the entire machine relative to the central hub making the UAV unit more “bottom heavy”, thus creating a pendulum effect, which is more stable in flight. | 05-26-2016 |
| 20160159473 | UNMANNED AERIAL VEHICLE AND OPERATIONS THEREOF - The present invention provides methods and apparatus for unmanned aerial vehicles (UAVs) with improved reliability. According to one aspect of the invention, interference experienced by onboard sensors from onboard electrical components is reduced. According to another aspect of the invention, user-configuration or assembly of electrical components is minimized to reduce user errors. | 06-09-2016 |
| 20160167778 | Unmanned Flying Device | 06-16-2016 |
| 20160176494 | SELF-RIGHTING FRAME AND AERONAUTICAL VEHICLE | 06-23-2016 |
| 20160185454 | UNMANNED AERIAL VEHICLE - Systems and methods are described herein related to an unmanned aerial vehicle, the unmanned aerial vehicle includes: a frame portion, two rear arms extending away from the frame portion, and at least one rear air propulsion device arranged on each of the rear arms at an orthogonal angle relative to a vertical axis. The at least one rear air propulsion device has an axis of rotation for both lift and rotation based on the angle. The unmanned aerial vehicle has two front arms arranged along a horizontal axis. The vertical axis is perpendicular to the horizontal axis. The unmanned aerial vehicle also includes at least one camera arranged on at least one of the front arms. The at least one camera faces a front direction. | 06-30-2016 |
| 20160194069 | THERMALLY CONDUCTIVE UNMANNED AERIAL VEHICLE AND METHOD OF MAKING SAME | 07-07-2016 |
| 20160200421 | CLEAN FUEL ELECTRIC MULTIROTOR AIRCRAFT FOR PERSONAL AIR TRANSPORTATION AND MANNED OR UNMANNED OPERATION | 07-14-2016 |
| 20160200432 | WEIGHT EFFICIENT SERVO ATTACHMENT SCHEME FOR RIGID COAXIAL ROTOR CONTROL SYSTEM | 07-14-2016 |
| 20160251077 | Small Flying Object | 09-01-2016 |
| 20160375997 | UNMANNED AERIAL VEHICLE WITH A TRI-WING CONFIGURATION - This disclosure describes a configuration of an unmanned aerial vehicle (UAV) that includes a substantially polygonal perimeter frame and a central frame. The perimeter frame includes a front wing, a lower rear wing, and an upper rear wing. The wings provide lift to the UAV when the UAV is moving in a direction that includes a horizontal component. The UAV may have any number of lifting motors. For example, the UAV may include four lifting motors (also known as a quad-copter), eight lifting motors (octo-copter), etc. Likewise, to improve the efficiency of horizontal flight, the UAV may also include one or more thrusting motors and corresponding thrusting propellers. When the UAV is moving horizontally, the thrusting motor(s) may be engaged and the thrusting propeller(s) will aid in the horizontal propulsion of the UAV. | 12-29-2016 |
| 20180022451 | UNMANNED AERIAL VEHICLE | 01-25-2018 |
| 20180022452 | MICRO HYBRID GENERATOR SYSTEM DRONE | 01-25-2018 |
| 20180022453 | Flying machine and flying unit | 01-25-2018 |
