An unmanned aerial vehicle for mounting a clamp to a line includes a body, a first propeller attached to the body, a second propeller attached to the body, and a third propeller attached to the body. The body is between at least one of the first propeller and the second propeller, the first propeller and the third propeller, or the second propeller and the third propeller. A guide is attached to the body and is configured to support the clamp for mounting to the line by flying the unmanned aerial vehicle toward the line. The guide is configured to support the clamp such that an imaginary clamp line between a first jaw of the clamp and a second jaw of the clamp when the clamp is in an arrested position is non-parallel to a plane intersecting the first propeller, the second propeller, and the third propeller.

A tail sitter aircraft is described, comprising a wing with a closed front section; a fuselage, from which said wing extends; said fuselage extending parallel to a first axis; said wing being a non-planar wing closed in on itself and without free ends; said wing comprising a first portion projecting from said fuselage, a second portion spaced from said first portion; and a first and a second connecting section, which are interposed between respective ends of said first portion and of said second portion, said first portion and said second portion being parallel to one another and extending parallel to a second axis orthogonal to said first axis, said first axis being arranged, in use, vertically in a take-off/landing position and inclined with respect to the vertical direction in a cruising position. Said first and a second connecting section extend parallel to a third axis orthogonal to said second axis and to said first axis, said wing comprising a third portion arranged on the opposite side of said first portion with respect to said second portion and connected to said first portion at their respective ends by first sections extending parallel to said third axis.

A tail sitter aircraft is described that comprises: a fuselage arranged vertically in a take-off/landing position and transversely to a vertical direction in a cruising position of the aircraft; a single wing; at least two first engines configured to exert respective first thrusts directed along respective first axes on the tail sitter; and at least two second engines rotating about respective second axes arranged above said first axes of the first engines, with reference to the cruising position; the at least two second engines being configured to exert respective second thrusts directed along respective second axes on the tail sitter; the first and second engines being carried by the single wing; the single wing comprises a first portion and a second portion mutually staggered from one another; the second portion being arranged above said first portion, with reference to said cruising position; said first portion comprises two half-wings, extending from opposite lateral sides of the fuselage; the wing further comprises a third portion arranged below said first portion with reference to said cruising position of said aircraft.

Various techniques are described utilizing unmanned aerial vehicles (UAVs, or “drones”) for various disaster and/or catastrophe-related purposes. An area at risk of an insurance-related event (catastrophe, hurricane, natural disaster, wild fire, etc.) that requires evacuation may be determined, as well as insured premises or assets within that area. With an insured's permission, drones may be directed to the area to collect image or other data of insured premises or assets before, during, or after the event strikes. The drone data may be received and analyzed to identify losses to insured assets that should properly be classified as theft losses for insurance purposes. Insurance claims may be prepared or adjusted for insureds based upon the theft losses in accordance with various types of insurance policies (auto, home, personal articles, etc.) or endorsements to ensure that insureds are properly and promptly reimbursed for the theft losses.

An aerial device includes a body, an optical system having gimbal supporting a camera, a lift mechanism coupled to the body, a haptic sensor coupled to the body and configured to generate haptic data, and a processing system disposed in the body and in data communication with the haptic sensor. The processing system is configured to process the haptic data to understand an intended position of the aerial device and/or an intended orientation of the gimbal and convert the intended position to a target position of the aerial device and/or the intended orientation to a target orientation of the gimbal utilizing said processed data irrespective of an initial position of said aerial device and an initial orientation of said gimbal. Also disclosed is a method for controlling the aerial device.

An aerial vehicle includes one or more propeller units operable to provide thrust for takeoff or hover flight and one or more propulsion units operable to provide thrust for forward flight. At least one propeller unit includes a shaft coupled to a motor, and a first propeller blade and a second propeller blade that are both connected to the shaft. The second propeller blade is located substantially opposite the first propeller blade, and the second propeller blade has a surface area substantially perpendicular to an axis of rotation that is greater than a corresponding surface area of the first propeller blade. While the aerial vehicle is in forward flight in a first direction and the motor is turned off, the first propeller blade and the second propeller blade are each configured to orient in a second direction that is substantially parallel to the first direction, such that the first propeller blade is oriented substantially upwind of the second propeller blade.

A drone frame includes first and second carbon fiber layers, and a center clear layer positioned between the first and second carbon fiber layers. A cutout is formed through an entire thickness of the first carbon fiber layer so as to expose a portion of the center clear layer. An LED unit is positioned in the cutout. The LED unit has a plurality of LEDs on a bottom thereof such that the LEDs abut the center clear layer. Light is transmitted from the LEDs through the center clear layer so as to illuminate the perimeter of the drone frame. A composite material used in the drone frame and a method of forming the composite material and drone frame are also disclosed.

A technique for operating an aerial vehicle involves enabling a vertical takeoff and landing (VTOL) propeller of the aerial vehicle to rotate freely. The VTOL propeller is coupled with a VTOL motor (e.g., a 3-phase brushless DC motor). The technique further involves detecting when the VTOL propeller rotates to a predefined position relative to a direction of flight for the aerial vehicle (e.g., when blades of the VTOL propeller extend along an axis that is parallel to the direction of flight). The technique further involves, in response to detecting that the VTOL propeller has rotated to the predefined position, providing a load from the VTOL motor that inhibits further rotation of the VTOL propeller. Accordingly, while the aerial vehicle is in fixed wing horizontal flight, the controller is able to align the VTOL propeller in the direction of horizontal flight to minimize drag from the VTOL propeller.

Unmanned aircraft systems (UASs) and related techniques are provided to improve the operation of unmanned mobile sensor or survey platforms. A flight altitude estimation system includes a logic device configured to communicate with a communication module and a flight barometer coupled to an unmanned aerial vehicle (UAV), wherein the communication module is configured to establish a communication link with a base station associated with the mobile platform, and the flight barometer is configured to provide flight pressures associated with the UAV as it maneuvers within a survey area. The logic device is configured to receive demark pressure data from a demark barometer coupled to the base station and determine a differential flight altitude estimation based, at least in part, on received flight pressure data and demark pressure data, a reference flight pressure and a reference demark pressure corresponding to a flight initiation location of the base station.

A seismic weight dropper arrangement for a drone. The arrangement comprises a winch assembly attachable to a drone and comprising an actuator and spool with a cable windable thereon. Arrangement also includes a seismic source assembly comprising a housing and a mass suspended within the housing via at least one resiliently elastic biasing element, such as a coil spring. The seismic source assembly is fast with the cable and the actuator configured selectively to eject the seismic source assembly from the drone under the influence of gravity. The resiliently elastic biasing element has a predetermined modulus of elasticity to facilitate the mass impacting the housing when the housing impacts a surface after such ejection from a predetermined height above the surface.