A method of inspection or maintenance of a curved ferromagnetic surface using an unmanned aerial vehicle (UAV) having a releasable crawler is provided. The method includes: flying the UAV from an initial position to a pre-perching position in a vicinity of the ferromagnetic surface; autonomously perching the UAV on the ferromagnetic surface; maintaining magnetic attachment of the perched UAV to the ferromagnetic surface; releasing the crawler from the magnetically attached UAV onto the ferromagnetic surface; moving the crawler over the curved ferromagnetic surface while maintaining magnetic attachment of the released crawler to the ferromagnetic surface; inspecting or maintaining the ferromagnetic surface using the magnetically attached crawler; and re-docking the released crawler with the perched UAV.

An unmanned aerial vehicle (UAV) configured to land, take off, and magnetically perch on a ferromagnetic cylindrical surface is provided. The UAV includes a body and articulated magnetic legs configured to land and magnetically perch the UAV on the cylindrical surface. Each magnetic leg has a fixed portion coupled to the body and a pivoting portion pivotably coupled to the fixed portion at a pivot axis. The pivoting portion includes a switchable magnet and a single articulation joint that provides the pivoting portion with a single degree of freedom about the pivot axis to passively orient the pivoting portion inward and tangent to the cylindrical surface in response to the pivoting portion contacting the cylindrical surface during the landing, and to passively maintain the inward orientation of the pivoting portion during the takeoff.

An unmanned aerial vehicle (UAV) configured to land, take off, and magnetically perch on a ferromagnetic cylindrical surface is provided. The UAV includes a body and articulated magnetic legs configured to land and magnetically perch the UAV on the cylindrical surface. Each magnetic leg has a fixed portion coupled to the body and a pivoting portion pivotably coupled to the fixed portion at a pivot axis. The pivoting portion includes a switchable magnet and a single articulation joint that provides the pivoting portion with a single degree of freedom about the pivot axis to passively orient the pivoting portion inward and tangent to the cylindrical surface in response to the pivoting portion contacting the cylindrical surface during the landing, and to passively maintain the inward orientation of the pivoting portion during the takeoff.

The invention relates to a propulsion device comprising a platform, a thrust unit, support means arranged to hold and support the thrust unit, integrally cooperating with the platform via one or more suitable mechanical connections, projecting means, integrally cooperating via suitable mechanical connections with the platform, a central foot, passing through the centre of inertia of the propulsion device and integrally cooperating via a suitable mechanical connection at its proximal end with the platform. In order to enable a landing of said propulsion device on receiving surfaces having relatively small dimensions with respect to the propulsion device and/or moving surfaces, the projecting means and the central foot are mutually arranged so that the central foot can provide the first contact between the device and a surface receiving the device.

The invention relates to a propulsion device comprising a platform, a thrust unit, support means arranged to hold and support the thrust unit, integrally cooperating with the platform via one or more suitable mechanical connections, projecting means, integrally cooperating via suitable mechanical connections with the platform, a central foot, passing through the centre of inertia of the propulsion device and integrally cooperating via a suitable mechanical connection at its proximal end with the platform. In order to enable a landing of said propulsion device on receiving surfaces having relatively small dimensions with respect to the propulsion device and/or moving surfaces, the projecting means and the central foot are mutually arranged so that the central foot can provide the first contact between the device and a surface receiving the device.

A landing station guidance-and-security system can include an environmental cover and/or a guide-and-security bar. In some embodiments, the landing station guidance-and-security system is integrated into a parcel-receiving device. In some embodiments, the landing station guidance-and-security system is configured to attach to a parcel-receiving device. In some embodiments, the guide-and-security bar includes a precision rod. In some embodiments, a drone landing station includes: a magnetic centering mechanism configured to center a drone and/or a package; sliding dovetail doors; a plow bar; at least one roll-up door; a first storage locker; a second storage locker; and/or a solid rear door configured to block access to the second storage locker from the first storage locker when the first storage locker is being accessed by a user.

An anchor for an aircraft. The anchor comprises a jack comprising a housing and a head that is able to move in translation in relation to the housing along an elevation axis, the head having three degrees of rotational freedom respectively about a longitudinal axis as well as a transverse axis and the elevation axis, the anchor comprising a member for taking up forces surrounding the jack and provided with a fastening suitable for being secured to the aircraft.

A control system for an aircraft, the system including a pilot input device configured to receive a pilot input, a plurality of sensors, each of the plurality of sensors positioned on a corresponding landing gear of the aircraft and configured to sense a parameter on the corresponding landing gear, and a controller in communication with the plurality of sensors, the controller configured to calculate an output command based on the pilot input and the sensed parameters of the landing gear, the output command including instructions for controlling a rotor of the aircraft.

An aircraft is provided. The aircraft includes a ducted wing portion and a fan chamber. The fan chamber is attached to a bottom of the ducted wing portion. A fan assembly is provided in the fan chamber and is operative to blow air through the ducted wing portion. The ducted wing portion is configured to direct air blown by the fan assembly down to provide lift for the aircraft.

A cargo aircraft configured to carry a portion of its payload in a cargo bay volume enclosed by a moveable nose door and supported by a structural extension of the fuselage that extends forward into the moveable nose door is disclosed. Examples include an aircraft with a continuous cargo bay extending from an aft end of a fixed portion into forward portion inside a nose door, where the portion of the cargo bay in the nose door is supported by a cantilevered support structure extending forward a length from a cargo opening into the fixed portion and such that the support structure extends into the nose door when the door is closed. The length of the support structure defines a supported cargo volume of at least about 15% of the overall volume of the fuselage forward of an aft end of the support structure.