A request for transport services that identifies a rider, an origin, and a destination is received from a client device. Eligibility of the request to be serviced by a vertical take-off and landing (VTOL) aircraft is determined based on the origin and the destination. A transportation system determines a first and a second hub for a leg of the transport request serviced by the VTOL aircraft and calculates a set of candidate routes from the first hub to the second hub. A provisioned route is selected from among the set of candidate routes based on network and environmental parameters and objectives including pre-determined acceptable noise levels, weather, and the presence and planned routes of other VTOL aircrafts along each of the candidate routes.

A computer-implemented method of enabling optimisation of derate for a propulsion system of a vehicle, the method comprising: determining a derate for the propulsion system of the vehicle using: an algorithm; a vehicle model defining path constraints for the vehicle through space; a propulsion system model defining parameters of the propulsion system; an objective function defining one or more objectives; and controlling output of the determined derate.

Methods, apparatus, and articles of manufacture for observer-based landing control of a vehicle are disclosed. An example apparatus includes at least one memory, and at least one processor to execute instructions to at least in response to determining an aircraft is in a flight plan flare regime, determine an estimate state of an aircraft parameter based on an execution of a transfer function of an observer model, the execution of the transfer function based on an altitude command corresponding to the flare regime, determine a gain value based on the aircraft parameter, determine an altitude control input based on the estimate state and the gain value, determine an altitude command output based on the altitude control input and longitudinal dynamics of the aircraft, the longitudinal dynamics generated in response to the aircraft executing the altitude command output, and control an elevator of the aircraft based on the altitude command output.

According to the present invention, a drone control system includes: a flying drone; a cloud server configured to transmit and receive information to and from the drone by wireless communication; and a ground control system configured to establish a flight plan of the drone by connecting the drone and the cloud server by the wireless communication.

Described are various embodiments of a flight management method and system using same. In one embodiment, a digital flight management system comprises: a digital processing environment comprising instructions to access: flight request data related to a flight plan; aircraft parameter data; a flight risk data source; and geographical data. The instructions are executable to: calculate a predicted flight path; digitally compare the predicted flight path with flight risk data from the flight risk data source to assess a flight risk associated with the predicted flight path; and display via a user interface the predicted fight path in accordance with the flight risk.

Systems and methods for dynamically adjusting a legend are provided. One system comprises a display unit; a user input device configured to receive a first input indicating a first altitude value; one or more processors; and a memory configured to store one or more programs, the one or more programs being configured for execution by the one or more processors and including instructions for: retrieving weather information corresponding to the first input; generating a command signal for displaying a legend having a color-code or shading-code associated with a plurality of attributes included in the retrieved weather information; and displaying the legend, on the display unit, in association with the retrieved weather information.

Methods and systems are provided for assisting operation of an aircraft when diverting from a flight plan using a comparative vertical profile display. A vertical profile display includes a first graphical representation of a first vertical profile corresponding to a first lateral route defined by a flight plan for the aircraft and a second graphical representation of a second vertical profile corresponding to a modified lateral route different from the first lateral route displayed concurrently on the vertical profile display. The first vertical profile corresponding to the first lateral route is depicted on the vertical profile display in a first plane and the second vertical profile corresponding to the modified lateral route is depicted on the vertical profile display in a second plane different from the first plane.

Systems and methods of detecting a vortex made by a travelling object is disclosed. Techniques include positioning a media collector to capture a visual media file of the vortex. In some configurations, a graphic recognition algorithm and vortex similarity engine are used to determine whether a visual media file captured by a media collector contains a vortex. In some configurations, a computer may trigger an alert if a travelling object vortex is not expected to be in the visual media file.

A system for providing maneuvering behaviors to a vehicle is disclosed. The system may include one or more controllers communicatively coupled to one or more vehicles. The one or more controllers may include one or more processors configured to execute one or more program instructions causing the one or more processors to: initiate one or more maneuver primitives in response to decision engine selection; receive a plurality of input parameters for the one or more maneuver primitives, the plurality of input parameters including one or more initialization definition input parameters, one or more goal definition input parameters, one or more navigation state input parameters, one or more design input parameters, and one or more vehicle performance envelope input parameters; and generate one or more control signals at one or more predetermined intervals of time to maneuver the one or more vehicles based on the decision engine selection.

Decision making support is provided. The method comprises receiving input of a current data file, wherein the current data file includes a valid time for features within the current data file. The valid time of the current data file is compared with Aeronautical Information Regulation and Control (AIRAC) cycle effective dates. Responsive to a discrepancy between the valid time of the current data file and the AIRAC cycle effective dates, the system determines if a feature change resulting from the discrepancy is flight critical. The feature change and a proposed solution with suggested text are displayed to a user in a dashboard. Responsive to input of agreement from the user to the proposed solution, the system automatically creates a change notice with the suggested text, a business process management ticket, and a data entry into a database.