This automatic takeoff/landing system for a vertical takeoff/landing aircraft comprises: a relative wind information acquisition unit that acquires the direction of relative wind at a moving object; and a control unit that executes takeoff/landing control to cause the vertical takeoff/landing aircraft to takeoff/land at a landing target point provided on the moving object. The control unit, during takeoff/landing of the vertical takeoff/landing aircraft, executes the takeoff/landing control on the basis of the direction of the relative wind acquired by the relative wind information acquisition unit, in a state in which the aircraft heading of the vertical takeoff/landing aircraft is caused to face the direction of the relative wind.

A method for determining a risk of landing failure of an aircraft on a landing location is based on a reference table constructed by making a selection of a set of values of M variables representative of landing conditions independent of potential turbulences, uniformly between a minimum value and a maximum value of each variable, performing a number P of closed-loop simulations by applying random turbulence conditions, from the set of values of the M variables, calculating a mean and a standard deviation of touchdown parameters from the P closed-loop simulations, and by complementing the reference table on each iteration for a number N of sets of values of the M variables. Next, the reference table is used to determine the risk of landing failure, in light of envisaged landing conditions.

A method includes selecting a landing waypoint on a runway and selecting a starting waypoint based on a location/heading of an aircraft relative to the runway. The method includes selecting additional waypoints between the starting waypoint and the landing waypoint. The starting and additional waypoints include latitude, longitude, and altitude variables. A sequence of waypoints from the starting waypoint to the landing waypoint via the additional waypoints indicates a desired location for the aircraft to traverse. The method includes generating location constraints for the starting and additional waypoints and generating an objective function for optimizing at least one of the variables. Additionally, the method includes generating a solution for the objective function subject to the location constraints. The solution includes latitude, longitude, and altitude values for the variables. The method further includes controlling the aircraft to traverse the starting and additional waypoints according to the latitude, longitude, and altitude values.

A method includes selecting a landing waypoint on a runway and selecting a starting waypoint based on a location/heading of an aircraft relative to the runway. The method includes selecting additional waypoints between the starting waypoint and the landing waypoint. The starting and additional waypoints include latitude, longitude, and altitude variables. A sequence of waypoints from the starting waypoint to the landing waypoint via the additional waypoints indicates a desired location for the aircraft to traverse. The method includes generating location constraints for the starting and additional waypoints and generating an objective function for optimizing at least one of the variables. Additionally, the method includes generating a solution for the objective function subject to the location constraints. The solution includes latitude, longitude, and altitude values for the variables. The method further includes controlling the aircraft to traverse the starting and additional waypoints according to the latitude, longitude, and altitude values.

Systems and methods for aircraft arrival management are disclosed. The system is configured to control a timing of landing between a leading and a trailing aircraft by calculating backward trajectories for each of the aircraft from a common touchdown point on a runway. The system is further configured to compute a delta distance, based on a separation threshold distance, corresponding to a travel distance for the trailing aircraft along an arc centered around a merge point, before turning towards a merge point.

Systems and methods for aircraft arrival management are disclosed. The system is configured to control a timing of landing between a leading and a trailing aircraft by calculating backward trajectories for each of the aircraft from a common touchdown point on a runway. The system is further configured to compute a delta distance, based on a separation threshold distance, corresponding to a travel distance for the trailing aircraft along an arc centered around a merge point, before turning towards a merge point.

An aircraft flap malfunction detection and landing assist system and method includes supplying flap status data, from a flap status data source, that indicates at least aircraft flap configuration and operability, supplying aircraft state data, from an aircraft state data source, that indicates at least aircraft weight, aircraft speed, and aircraft position, supplying weather data, from a weather data source, that indicates current weather at a landing runway, processing, in a processing system the flap status data to determine if at least one flap is inoperable and, upon determining that the at least one flap is inoperable, processing the flap status data, the aircraft state data, and the weather data to selectively generate, and command a display device to render, at least one of forward slip landing parameters or side slip landing parameters.

A method for supporting aerial operation includes obtaining a real-time location of an aircraft, obtaining a location of a supply station, obtaining a location of a next waypoint, and controlling the aircraft based on a status parameter related to a flight status of the aircraft associated with the real-time location of the aircraft. Controlling the aircraft includes controlling, in response to the status parameter satisfying a first preset condition, the aircraft to fly to the next waypoint; and controlling, in response to the status parameter satisfying a second preset condition, the aircraft to fly to the supply station.

A method of aligning an aircraft with a landing platform in motion comprises measuring a GPS heading with at least one GPS sensor positioned at a known location relative to the landing platform while the landing platform is in motion, measuring an orientation of the aircraft with an orientation sensor fixed relative to the aircraft, calculating an orientation of the landing platform from the GPS heading, calculating an orientation offset between the measured orientation of the aircraft and the calculated orientation of the landing platform, and changing an orientation of the aircraft or the landing platform to reduce the orientation offset. A system for landing and securing an aircraft in an enclosure, a system for disconnecting a tether from an aircraft, and a system for landing an aircraft in an enclosure are also described.

A system for facilitating navigation of an aircraft comprises one or more processors and a memory coupled to the processors. The memory stores data into a data store and program code that, when executed by the processors, causes the system to detect an infrared site signal indicating a site code transmitted by one or more infrared beacons that form a beacon network around a site. The site code represents a site. In response to detecting the infrared site signal, the system determines the site indicated by the site code. The system searches for two or more infrared beacon signals and detects the two or more infrared beacon signals. In response to detecting the two or more infrared beacon signals, the system determines a location of the aircraft based on the two or more infrared beacon signals.