One or more potential drone and/or flying car (DFC) corridors are identified based on the topology of a road network. Trajectories traveled by vehicles are determined from a plurality of instances of probe data received from a plurality of vehicle apparatuses onboard the vehicles. A volume of traffic for a path through the road network and corresponding to a potential DFC corridor is determined based on the trajectories. A delay metric for the path through the road network and corresponding to the potential DFC corridor is determined based on the trajectories. A traffic metric is then determined for the path based on a combination of the volume of traffic, the delay metric and a measure of the topology of the road network. The one or more potential DFC corridors are ranked by their corresponding traffic metrics.

A system and method for autonomously controlling a set of unmanned aerial vehicles is provided. The autonomous ground control system may include a communications module and a fleet configuration module in communication with one or more user interface applications. The autonomous ground control system may receive one or more flight commands and generate fleet configuration instructions and safety information. The autonomous ground control system may provide the fleet configuration instructions to each unmanned aerial vehicle in the set in order to carry out the fleet configuration instructions in real time.

A drone docking ports (DDP) mounted on a pole top in close proximity to an accident scene with an openable and closable enclosure, a docking plate having integrated battery wired or wireless recharging pads, and a control module (CM) is disclosed. The CM is adapted to autonomously control all functions of the DDP including actuation of the enclosure and relay of video, audio, and flight control information between the CM and a central monitoring center and/or emergency personnel. A drone with a top and bottom profile design allowing numerous drones to be stacked upon one another and store in the DDP. When the DDP enclosure is in an open position, a drone or stack of drones may initiate a flight from the DDP and to re-dock the drone or stack of drones when the flight is completed, the enclosure may be closed to protect the drone or stack of drones.

Systems and methods for a weapon mountable tactical heads-up display (HUD) are provided. The HUD may include a 9 degrees of freedom (9DOF) sensor, a target library, and a target finder visualization. The target library may store respective ballistic information for each target of a plurality of targets. The respective ballistic information may include a target vector for each target of the plurality of targets. The target vector may be calculated based on data received from the 9DOF sensor. The target finder visualization may allow a shooter to locate a selected target of the plurality of targets. The target finder visualization may be based on the target vector.

In an aspect, a system for a guidance interface for a vertical take-off and landing (VTOL) aircraft comprises a plurality of flight components that are mechanically coupled to the VTOL aircraft. The VTOL aircraft also comprises an output device that is configured to present a display of the outside environment. The output device may overlay the display with a datum, a focal point, and a guidance symbol. The datum may be associated with the flight components of the VTOL aircraft. The focal point may be indicative of a desired landing location for the VTOL aircraft. The focal point may be determined by at least a predetermined flight plan. The guidance symbol may be a symbol that includes an optimal flight path to the focal point.

An autonomous unmanned aerial vehicle for land, sea and air use. The autonomous unmanned aerial vehicle is more specifically related to an unmanned aerial vehicle, wherein the autonomous unmanned aerial vehicle is configured to vertically take off and vertically land, fly with fixed wings and stay in the air silently for a long time by means of a balloon inflated behind it.

A rotorcraft is described and includes an inertial measurement unit (“IMU”) sensor mounted to the rotorcraft, the IMU sensor oriented relative to the rotorcraft such that a roll attitude of the rotorcraft occurs about a Z-axis and has a range of ±90 degrees, a pitch attitude of the rotorcraft occurs about an X-axis and has a range of ±180 degrees, and a yaw attitude of the rotorcraft occurs about a Y-axis and has a range of ±180 degrees.

An electronic vertical takeoff and landing (eVTOL) multicopter which includes a communications interface configured to establish a communication channel between a site local server and the eVTOL multicopter and send a vehicle identifier and vehicle state information from the eVTOL multicopter to the site local server. The eVTOL multicopter also includes a processor configured to perform a management operation received from the site local server, wherein the site local server is configured to determine the management operation based at least in part on the vehicle identifier and the vehicle state information.

A flight vehicle is allowed to safely fly even in a wireless communication unavailable area or the like where the flight vehicle cannot report its own location. Control is performed to limit the flight vehicles that enter exclusive controlled airspace including an area where the flight vehicles cannot report their own locations. In a case where the controlling control unit receives an entry application from one of the flight vehicles that seeks to enter the exclusive controlled airspace, the controlling control unit transmits entry permission to the one of the flight vehicles when none of the flight vehicles other than the one of the flight vehicles has entered the exclusive controlled airspace. Furthermore, in this case, for example, when any of the flight vehicles other than the one of the flight vehicles has entered the exclusive controlled airspace, a standby instruction is transmitted to the one of the flight vehicles.

A system can include a flight controller for an aircraft that includes an electric motor that drives blades with a variable pitch, where the flight controller receives a command to change a flight characteristic of the aircraft and creates a torque command and a revolutions per minute (RPM) command. The system can also include a propulsion assembly, where the propulsion assembly creates a current command based at least in part on the torque command and the RPM command, creates a blade pitch command based at least in part on the torque command and the RPM command, communicates the current command to the electric motor to change a mechanical output of the electric motor, and communicates the blade pitch command to blade actuators to control the pitch of the blades. The current command and the blade pitch command cause the blades of the aircraft to rotate at a predetermined RPM.