FIELD: transport.
SUBSTANCE: invention relates to aircraft engineering, particularly, to rotorcraft engine control systems. Proposed device (5) comprises computer unit (10) and display unit (20). Computer unit (10) executes memorised instructions to define at least one propeller thrust reserve (ΔP) between current thrust developed by said propeller and threshold thrust corresponding to the limit of negative power (Pmin) and to define the main minimum general angle of aircraft path inclination to earth surface to be followed by descending rotorcraft depending upon said thrust reserves (ΔP). Computer unit outputs the main symbol (25) of the main minimum general angle of aircraft path inclination to earth surface to be followed by descending rotorcraft (1) to display (20). Note here that said main symbol (25) displays as an imposition on the image (21) of surroundings ahead of rotorcraft (1) to ensure safe descending of rotorcraft.
EFFECT: perfected flight control system.
12 cl, 3 dwg
