FIELD: aviation.
SUBSTANCE: aircraft vertical elevation and landing safety system comprises an altitude sensor, an accelerometer, a gyroscope, electronic stroke controllers (ESC), electric motors of rotors, an on-board flight computer configured to process information from altitude-velocity parameters sensors and its comparison with predetermined threshold permissible values, formation of control signals of electric motors of rotors in a certain manner and attenuation of signals in case of transition of threshold values.
EFFECT: limitation of pitch, roll and yaw angles, horizontal speed during takeoff and landing, higher flight stability, increased safety of pilot and surrounding objects.
1 cl, 1 dwg
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