The present disclosure provides a control method of a UAV, a control device of a UAV, and a computer-readable storage medium, and relates to the technical field of UAVs. The control method of a UAV includes: determining a deviation between a vertical mapping point on the ground and a landing point of the UAV, the deviation comprising a deviation in a horizontal axis direction of a camera coordinate system and a deviation in a vertical axis direction of the camera coordinate system; and generating speed control amounts of the UAV in the horizontal axis direction and the vertical axis direction of the camera coordinate system by a controller, using the deviation in the horizontal axis direction and the deviation in the vertical axis direction.

Systems and methods for detection and display of marine objects for an aircraft. One example system includes a transceiver configured to communicate with an Automatic Identification System (AIS) server and an electronic controller located within an aircraft. The electronic controller is configured to provide on a display an interface comprising a map representing a travel area. The electronic controller is configured to provide, on the map, a first graphical representation of the aircraft within the travel area. The electronic controller is configured to receive, via the transceiver, marine object data from the AIS server. The electronic controller is configured to periodically update, on the map, a second graphical representation of a first marine object within the travel area based on the marine object data.

A landing zone landing assistance system for a rotary wing aircraft, the system includes a computer, an HMI for interacting with the pilot of the aircraft, an optical assembly provided with at least one optical sensor, a radar assembly provided with at least one radar detector and an inertial unit, wherein the computer is configured to implement the following steps: a first step (Step1) consisting in determining an optical image of the possible landing zone; a second step (Step2) consisting in determining the relative position of the landing zone with respect to said system in the terrestrial reference frame; a third step (Step3) consisting in determining a landing zone approach path; and a fourth step (Step4) consisting in supplying to the HMI a deviation between the position of the system and the approach path.

A landing zone landing assistance system for a rotary wing aircraft, the system includes a computer, an HMI for interacting with the pilot of the aircraft, an optical assembly provided with at least one optical sensor, a radar assembly provided with at least one radar detector and an inertial unit, wherein the computer is configured to implement the following steps: a first step (Step1) consisting in determining an optical image of the possible landing zone; a second step (Step2) consisting in determining the relative position of the landing zone with respect to said system in the terrestrial reference frame; a third step (Step3) consisting in determining a landing zone approach path; and a fourth step (Step4) consisting in supplying to the HMI a deviation between the position of the system and the approach path.

A landing system for an aircraft and a method of calculating a reference path. The landing system can calculate a reference path for use during a non-precision approach to a runway, the reference path including a course, flight path angle, and anchor point. The anchor point has a longitude, a latitude and an altitude. The landing system is configured to extract from a navigation database a missed approach point corresponding to a first landing threshold point of the runway. The missed approach point has a longitude, a latitude and an altitude. The landing system is configured such that calculation of the reference path includes setting the altitude of the anchor point with use of the altitude of the missed approach point. The system may be used when approaching a runway having a displaced landing threshold point, the location of the point not being stored in the navigation database.

A landing system for an aircraft and a method of calculating a reference path. The landing system can calculate a reference path for use during a non-precision approach to a runway, the reference path including a course, flight path angle, and anchor point. The anchor point has a longitude, a latitude and an altitude. The landing system is configured to extract from a navigation database a missed approach point corresponding to a first landing threshold point of the runway. The missed approach point has a longitude, a latitude and an altitude. The landing system is configured such that calculation of the reference path includes setting the altitude of the anchor point with use of the altitude of the missed approach point. The system may be used when approaching a runway having a displaced landing threshold point, the location of the point not being stored in the navigation database.

Systems of enhancing contrast of lighting can include a light-transmitting subsystem having a light source to emit a stream or light-signal pulses and an encoding circularly polarizing filter to optically encode the stream of light-signal pulses with circular polarization, and a light-receiving subsystem including a decoding circularly polarizing filter to optically decode the circular polarization of the stream of light-signal pulses and a light imager to receive the stream of light-signal pulses after being optically decoded by the decoding circularly polarizing filter. In another example, the system can include a polarimetric light imaging assembly, a light source to generate a stream of light-signal pulses directed at the polarimetric light imaging assembly, and a control system to synchronously control the light-signal pulses to be emitted from the light source in timed correlation with a component(s) of the polarimetric light imaging assembly.

Systems of enhancing contrast of lighting can include a light-transmitting subsystem having a light source to emit a stream or light-signal pulses and an encoding circularly polarizing filter to optically encode the stream of light-signal pulses with circular polarization, and a light-receiving subsystem including a decoding circularly polarizing filter to optically decode the circular polarization of the stream of light-signal pulses and a light imager to receive the stream of light-signal pulses after being optically decoded by the decoding circularly polarizing filter. In another example, the system can include a polarimetric light imaging assembly, a light source to generate a stream of light-signal pulses directed at the polarimetric light imaging assembly, and a control system to synchronously control the light-signal pulses to be emitted from the light source in timed correlation with a component(s) of the polarimetric light imaging assembly.

Embodiments of the present disclosure assist pilots of aerial vehicles in performing particular operations utilizing improved user interface(s). In some contexts, pilots performing vertical takeoffs or vertical landings cannot visually inspect the environment around the vehicle. Embodiments of the present disclosure utilize virtual elements, including a virtual corridor and virtual vehicle corresponding to an aerial vehicle, to enable improved visualization and control of an aerial vehicle within a particular environment. Utilizing representation(s) of the virtual elements, including a virtual corridor and/or virtual vehicle, embodiments of the present disclosure provide improved user interfaces that assist a pilot in safely controlling an aerial vehicle (even without visual inspection of a real-world environment) during vertical takeoff and/or vertical landing.

Methods and apparatus are provided for generating a runway landing alert for an aircraft. The method comprises establishing an altitude parameter and a safety envelope for a designated target runway of the aircraft. A track of the aircraft is monitored with reference to a centerline of the target runway. Any deviation by the aircraft from the centerline of the target runway is detected and determined if it is within a margin of error. If the deviation is within the margin of error, an altitude parameter is increased. If the aircraft is determined to still be maneuvering with respect to the centerline of the target runway, the altitude parameter is decreased. Otherwise, an alert is generated if the aircraft is outside of the safety envelope.