Landing zone landing assistance system for a rotary wing aircraft

A helicopter provided with a landing zone landing assistance system for a rotary wing aircraft, the system comprising 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) comprising determining an optical image of the possible landing zone based on the data supplied by the optical assembly, the possible landing zone representing the intersection of the field of the optical assembly and of the field of the radar assembly, and in transmitting this image to the HMI allowing the pilot to select a landing zone, on the possible landing zone reduced to said intersection;
• a second step (Step2) comprising determining the relative position of the landing zone with respect to said system in the terrestrial reference frame, based on the landing zone supplied by the HMI selected by the pilot, in the possible landing zone, on data supplied by the inertial unit, on data supplied by the optical assembly, and on data supplied by the radar assembly:
• a third step (Step3) comprising determining a landing zone approach path based on the relative position of the landing zone with respect to said system and on approach parameters supplied by the HMI on instructions from the pilot;
• and
• a fourth step (Step4) comprising supplying to the HMI a deviation between the position of the system and the approach path, based on data supplied by the inertial unit, on data supplied by the radar assembly, and on the relative position of the landing zone.

A drone provided with a landing zone landing assistance system for a rotary wing aircraft, the system comprising 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) comprising determining an optical image of the possible landing zone based on the data supplied by the optical assembly, the possible landing zone representing the intersection of the field of the optical assembly and of the field of the radar assembly, and in transmitting this image to the HMI allowing the pilot to select a landing zone, on the possible landing zone reduced to said intersection;
• a second step (Step2) comprising determining the relative position of the landing zone with respect to said system in the terrestrial reference frame, based on the landing zone supplied by the HMI selected by the pilot, in the possible landing zone, on data supplied by the inertial unit, on data supplied by the optical assembly, and on data supplied by the radar assembly:
• a third step (Step3) comprising determining a landing zone approach path based on the relative position of the landing zone with respect to said system and on approach parameters supplied by the HMI on instructions from the pilot;
• and
• a fourth step (Step4) comprising supplying to the HMI a deviation between the position of the system and the approach path, based on data supplied by the inertial unit, on data supplied by the radar assembly, and on the relative position of the landing zone.