A system, method and computer program product for controlled drone descent, and deactivation, including a drone deactivation system; and a location system. The drone deactivation system calculates positioning, signal reception, signal strength, and signal identification parameters of a target drone from the location system, and determines an attack method based on the calculated parameters. The drone deactivation system employs the determined attack method against the target drone for forcing at least one of controlled drone descent, and deactivation of the target drone.

A system, method and computer program product for controlled drone descent, and deactivation, including a drone deactivation system; and a location system. The drone deactivation system calculates positioning, signal reception, signal strength, and signal identification parameters of a target drone from the location system, and determines an attack method based on the calculated parameters. The drone deactivation system employs the determined attack method against the target drone for forcing at least one of controlled drone descent, and deactivation of the target drone.

An aeronautical vehicle that rights itself from an inverted state to an upright state has a self-righting frame assembly has a protrusion extending upwardly from a central vertical axis. The protrusion provides an initial instability to begin a self-righting process when the aeronautical vehicle is inverted on a surface. A propulsion system, such as rotor driven by a motor can be mounted in a central void of the self-righting frame assembly and oriented to provide a lifting force. A power supply is mounted in the central void of the self-righting frame assembly and operationally connected to the at least one rotor for rotatably powering the rotor. An electronics assembly is also mounted in the central void of 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 surface.

A system and method for remote control of a mobile device is provided herein. The system includes a primary receiver for providing primary command and control of the mobile device; a secondary receiver for providing secondary command and control of the mobile device; the mobile device configured to respond to command and control signals sent by any of the primary receiver and the secondary receiver; and a relay platform for relaying the command and control signals throughout the system. The primary receiver may include an extended reality component.

A system and method for remote control of a mobile device is provided herein. The system includes a primary receiver for providing primary command and control of the mobile device; a secondary receiver for providing secondary command and control of the mobile device; the mobile device configured to respond to command and control signals sent by any of the primary receiver and the secondary receiver; and a relay platform for relaying the command and control signals throughout the system. The primary receiver may include an extended reality component.

A ground state determination system for an aircraft includes sensors configured to detect parameters of the aircraft and a flight control system implementing a ground state module. The ground state module includes a ground state monitoring module configured to monitor the parameters and a ground state determination module configured to compare each of the parameters monitored by the ground state monitoring module to a respective parameter threshold to determine whether the aircraft is on a surface.

The present disclosure according to at least one embodiment provides a a method for managing, by a computing device, a flight plan of an unmanned aerial vehicle, the method comprising: receiving input information including a departure location and a destination of the unmanned aerial vehicle, inputting the input information into a pre-constructed artificial intelligence model, acquiring at least one of a travel path, a takeoff scheme, an altitude climb scheme at the departure location, an arrival scheme at the destination, or a landing scheme on the destination from the artificial intelligence model, and providing a flight plan including the acquired at least one of the travel path, the takeoff scheme, the altitude climb scheme at the departure location, the arrival scheme as the destination, and the landing scheme on the destination.

Systems and methods for sensorless motor control may include a back EMF (electromotive force) observer, an adaptive EMF filter, magnitude compensation, hybrid rotor position and speed determination, rotor position and speed blending, and angle compensation. In order to provide accurate and reliable rotor position and speed estimations for a motor over a wide and varied range of speeds, at low speeds, during speed reversals, and/or in the presence of external forces, loads, or torques, the sensorless motor control may utilize a hybrid rotor position and speed determination that leverages both angle-based and magnitude-based methods. Further, the outputs of the two methods may be blended based on a shaping function to generate a final estimated rotor position and speed. Then, the motor may be more accurately and reliably controlled based on the final estimated rotor position and speed.

A tailsitter aircraft includes an airframe, a thrust array attached to the airframe and a flight control system. The thrust array includes propulsion assemblies configured to transition the airframe from a forward flight orientation to a VTOL orientation at a conversion rate for an approach to a target ground location in a forward flight-to-VTOL transition phase. The flight control system implements an adaptive transition system including a transition parameter monitoring module configured to monitor parameters including a ground speed and a distance to the target ground location. The adaptive transition system includes a transition adjustment determination module configured to adjust the conversion rate of the airframe from the forward flight orientation to the VTOL orientation based on the ground speed and the distance to the target ground location such that the airframe is vertically aligned with the target ground location in the VTOL orientation of the forward flight-to-VTOL transition phase.

An unmanned aerial vehicle and a landing method for unmanned aerial vehicle are provided. The unmanned aerial vehicle includes a positioning device and a processor. When the processor detects a fight status of the unmanned aerial vehicle, the processor obtains a current coordinate from the positioning device. According to the current coordinate, a predetermined route, and a plurality of emergency landing coordinates, the processor calculates a plurality of distances for the unmanned aerial vehicle moving from the current coordinate to each of the emergency landing coordinates along the predetermined route. According to a shortest distance among the plurality of distances, the processor obtains a target emergency landing coordinate. The processor controls the unmanned aerial vehicle to move to the target emergency landing coordinate along the predetermined route.