| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 244170170 | With landing, mooring, or nonaerial propelling or steering gear | 15 |
| 20100308156 | Split Pivot Fitting for Helicopter Landing Gear - A multi-piece pivot fitting for use on aircraft with skid type landing gear has a forward fitting, and aft fitting, and at least a lower strap. This configuration allows cross tube loads to be transferred to the keel beams of the aircraft, thereby allowing selected longitudinal rocking of the aircraft and preventing the aircraft from going into a resonance state. | 12-09-2010 |
| 20100320313 | COMBINED HELICOPTER LANDING PAD AND CLAMSHELL ENCLOSURE - A clamshell case for enclosing a helicopter includes a base for supporting said helicopter, a first side section attached by a first hinge to one edge of the base, a second side section attached by a second hinge to the other edge of the base, and a drive system for rotating said side sections towards each other to substantially enclose said helicopter and substantially completely protect it from the weather and other damage. | 12-23-2010 |
| 20110155845 | RETRACTABLE HELICOPTER LANDING GEAR - A retractable helicopter landing gear has a suspension structure supporting one wheel, and is movable between a withdrawn position, to reduce drag on the helicopter, and a lowered position for landing and takeoff of the helicopter. The landing gear also has a skid, which is located between the axis of rotation of the wheel and the periphery of the wheel, is diametrically opposite the suspension structure, and is connected to the suspension structure by a connecting device having a torsion bar. | 06-30-2011 |
| 20110233323 | SKID-TYPE LANDING GEAR FOR A HELICOPTER - The invention relates to a skid-type landing gear ( | 09-29-2011 |
| 20120037750 | Airlift - The airlift comprises an engine-propeller unit and means for retention of the engine-propeller unit relative to the earth's surface, fixed on the above unit in the axis of rotation upward of the center of gravity of the engine-propeller unit. The means for retention of the engine-propeller unit relative to the earth's surface comprise solely a wire rope or a wire rope and an arm fixed inside the engine-propeller unit, or a wire rope and a frame embracing the engine-propeller unit fully or partially. | 02-16-2012 |
| 20130214088 | AERIAL UNIT AND METHOD FOR ELEVATING PAYLOADS - An aerial unit includes a connecting element arranged to connect a ground unit to the aerial unit. The ground unit may include a connecting element manipulator, for altering an effective length of the connecting element and a ground unit controller for controlling the connecting element manipulator. A positioning unit is arranged to image the aerial unit and to generate metadata about a location of the aerial unit. An interfacing module is provided for coupling a payload to the aerial unit. At least one of the ground unit and the aerial unit may include a controller that is arranged to control, at least in response to the metadata, at least one of a first propeller motor and at least one steering element to affect at least one of the location of the aerial unit and the orientation of the aerial unit. | 08-22-2013 |
| 20130341457 | SEMI-LEVERED ARTICULATED LANDING GEAR SYSTEM - The landing gear system for an aircraft includes a shock strut assembly that is coupled to the airframe with a universal joint. A tire member is mounted to the shock strut assembly. The landing gear system also includes a drag brace assembly coupled to an airframe of the aircraft with a spindle, the spindle being rotatable about a spindle axis. A radius rod is rotatably coupled to the airframe of the aircraft. The radius rod and the shock strut assembly are retractable about a retraction rotation axis. Further, the spindle axis has a common intersection point with the centerline axis and the retraction rotation axis. The orientation of the spindle axis causes a translation of the tire member to have a longitudinal component during a compression of the shock strut assembly. | 12-26-2013 |
| 20140034775 | VEHICLE CAPABLE OF STABILIZING A PAYLOAD WHEN IN MOTION - In specific embodiments, a vehicle propellable through fluids comprises a main work section and a plurality of propulsion units. The main work section includes a payload support hub, a payload support structure rotatable in 360° about the payload support hub in at least one axis, and a core including at least one microprocessor, the core at least partially nested within the payload support hub. The at least one microprocessor is adapted to substantially maintain an orientation of the payload support structure relative to a horizon line as the vehicle is propelled. One or more payloads are mountable on the rotatable payload support structure. | 02-06-2014 |
| 20140034776 | VEHICLE CAPABLE OF IN-AIR AND ON-GROUND MOBILITY - In specific embodiments, a vehicle propellable through fluids or along surfaces, comprises a main work section and a plurality of propulsion units for propelling the main work section. The main work section supports one or more payloads. The propulsion units each include a rotor system and a ring-shaped wheel at least partially arranged about the rotor system and rotatable about the rotor system. The ring-shaped wheel is arranged at a banked angle relative to the rotor system. | 02-06-2014 |
| 20140217230 | DRONE CARGO HELICOPTER - A drone cargo helicopter having an elongated body. The elongated body has a low profile and has a front portion, a rear portion, an upper surface, a lower surface and a pair of opposing sides extending between the front and the rear portions. At least a first blade set is coupled to the upper surface and rotating in a first direction. Two or more struts are pivotally coupled to opposing sides or lower surface of the elongated body, the struts being coupled via a joint at a top end of the strut. The lower surface of the elongated body comprises a substantially planar surface between the front and rear portions, the substantially planar surface having one or more attachments to provide a rigid engagement with a container. The struts are pivotally movable between a first position and a second position, wherein in the first position, the struts support the elongated body a distance from a ground surface that is greater than a height of the container. | 08-07-2014 |
| 20140353421 | CABLE-TETHERED HELICOPTER SURVEILLANCE SYSTEM - The invention aims to transfer a substantial volume of high-quality, high-volume real-time data, which currently cannot be achieved by wireless techniques, between a mobile airborne observation platform and the ground station via a tethered fiber connection between said platform and said ground station. | 12-04-2014 |
| 20150069174 | 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. | 03-12-2015 |
| 20160176520 | SELF-ENCLOSED AIR VEHICLE | 06-23-2016 |
| 20160375979 | AIRCRAFT STRUCTURAL COMPONENT THAT IS ADAPTED FOR ABSORBING AND TRANSMITTING FORCES IN AN AIRCRAFT - An aircraft structural component that is adapted for absorbing and transmitting forces in an aircraft, the aircraft structural component comprising at least one panel element and at least one reinforcing structure. The at least one reinforcing structure is rigidly attached to the at least one panel element such that at least one cavity is defined between the at least one panel element and the at least one reinforcing structure, the at least one cavity being adapted for distributing forces that are absorbed by the aircraft structural component in operation. | 12-29-2016 |
| 20220135251 | FLYING VEHICLE SYSTEMS AND METHODS - An example charging station for an unmanned aerial vehicle (UAV), the charging station generally including a nest and a charging device. The nest includes an upper portion and a lower portion. The upper portion defines an upper opening sized and shaped to receive a landing apparatus of the UAV, and a diameter of the nest reduces from a first diameter at the upper opening to a second diameter at the lower portion. The charging device is mounted in the nest, and includes a first contact pad and a second contact pad. The charging device is configured to apply a voltage differential across the first contact pad and the second contact pad such that the charging station is operable to charge a power supply of the UAV via the landing apparatus. | 05-05-2022 |
