Systems, apparatuses, and methods are provided herein for stabilizing an unmanned aerial system. An apparatus for stabilizing an unmanned aerial system comprises a ring member and a pair of attachment members each having a first end and a second end, the first end being configured to attach to a multicopter and a second end being coupled to the ring member. Wherein the pair of attachment members holds the ring member such that a plane of a circumference of the ring member is generally parallel to blades of the multicopter.

An unmanned aerial vehicle (UAV) includes a fuselage, a pair of wings attached to the fuselage, and a propulsion system mounted to the wings to provide propulsion to the UAV. The fuselage has an outer fuselage shell that is a first mechanical support structure for an airframe of the UAV. The pair of wings is attached to the fuselage and shaped to provide aerodynamic lift. The wings have outer wing shells that are second mechanical support structures for the airframe. The outer fuselage shell or the outer wing shells comprise one or more formed-metal sheets.

An unmanned aerial vehicle (UAV) includes a fuselage, a pair of wings attached to the fuselage, and a propulsion system mounted to the wings to provide propulsion to the UAV. The fuselage has an outer fuselage shell that is a first mechanical support structure for an airframe of the UAV. The pair of wings is attached to the fuselage and shaped to provide aerodynamic lift. The wings have outer wing shells that are second mechanical support structures for the airframe. The outer fuselage shell or the outer wing shells comprise one or more formed-metal sheets.

A mechanical joiner for an airframe includes a joiner core and first and second caps. The joiner core has a first side with a first cradle shaped to hold a first structural member and a second side with a second cradle shaped to hold a second structural member. The first cap is shaped to mate to the first side and clamp the first structural member into the first cradle. The joiner core includes a first hole for a first mechanical fastener to extend through and across the first cradle and secure the first cap to the joiner core. The second cap is shaped to mate to the second side and clamp the first structural member into the second cradle. The second cap includes second holes for second mechanical fasteners, distinct from the first mechanical fastener, to secure the second cap to the joiner core.

An introduced autonomous aerial vehicle can include multiple cameras for capturing images of a surrounding physical environment that are utilized for motion planning by an autonomous navigation system. In some embodiments, the cameras can be integrated into one or more rotor assemblies that house powered rotors to free up space within the body of the aerial vehicle. In an example embodiment, an aerial vehicle includes multiple upward-facing cameras and multiple downward-facing cameras with overlapping fields of view to enable stereoscopic computer vision in a plurality of directions around the aerial vehicle. Similar camera arrangements can also be implemented in fixed-wing aerial vehicles.

A multicopter equipped with a fall prevention device enabling it to prevent the airframe from falling even in case the multicopter has become unable to fly normally for various reasons. A multicopter includes a multicopter main body having rotors which are driven by a power source, a plurality of emergency rotors which are driven by an emergency power source which is different from the power source, abnormality detection sensors for detecting abnormality of the multicopter main body, and an emergency control device, the multicopter being configured such that, when the abnormality detection sensors have detected abnormality of the multicopter main body, the emergency control device performs control to deactivate operation of the rotors and drive the emergency rotors by the emergency power source to prevent a rapid fall of the multicopter.

A multi-rotor aircraft (100) is provided, comprising: a main aircraft assembly (10) comprising a first magnetic medium (13), a main housing (11), and a control motherboard accommodated in the main housing (11), wherein the first magnetic medium (13) is provided on the main housing (11), a slot (1120) is further provided on the main housing (11), and a connection point of the control motherboard is provided in the slot (1120); and a plurality of rotor systems (20), wherein each of the plurality of rotor systems comprises a second magnetic medium (23), a rotor mechanism (21), and a rotor protection cover (22) that is of a hollow annular structure and is fixed outside the rotor mechanism (21), wherein the second magnetic medium (23) is fixed to the rotor protection cover (22) and attracting the first magnetic medium (13), and a pin (2200) matching the slot (1120) is further provided on the rotor protection cover (22). The rotor systems (20) can be quickly mounted on or dismounted from the main aircraft assembly (10), thereby achieving the technical effects of shortening the mounting and dismounting time and improving the operation efficiency.

A process for controlling a plurality of mobile-radio equipped robots in a talkgroup includes receiving, at a mobile-radio equipped robot via a wireless communications interface comprising one of an infrastructure wireless communication interface for communicating with an infrastructure radio access network (RAN) and an ad-hoc wireless communication interface for communicating with an ad-hoc network, a group voice call containing a voice-command. The mobile-radio equipped robot determines that it is a target of the group voice call, and responsively text-converts the voice-command into an actionable text-based command. The mobile-radio equipped robot subsequently operates a mechanical drive element in accordance with the actionable text-based command.

A flying machine frame structural body including: a frame that surrounds a flying machine body including a rotating blade, and to which the flying machine body is fixed; and plural wheels that are rotatably supported by the frame.

A system for payload delivery and drone recovery, wherein the system functions with the use of a lightweight parachute and a directional control module. The system can include a drop system for payload delivery, wherein the drop system releases the parachute and payload upon reaching a target site. The system can also include a recovery system, wherein the recovery system deploys the parachute and steers the failed drone to a target site. A lightweight ram-air parachute is used to provide a lighter steerable parachute system.