FIELD: control of flying vehicle motion. SUBSTANCE: control signal to elevator actuator is shaped in form of sum of signals proportional to difference of present and programmed magnitudes of rate of pitch and integral of this difference. Rudder control signal Grud is simultaneously measured which defines dynamics of flying vehicle in lateral motion; then absolute value of this signal is compared with magnitude corresponding to latching the rudder stop σlim which is indicative of danger of overrunning the runway; in case σlim< Grud, the programmed magnitude of rate of pitch is zeroed. EFFECT: high safety of run of flying vehicle over runway at reduced coefficient of contact of runway (moist, wet, covered with ice), as well as in case of derangement of brake wheels of main landing gear struts. 2 dwg
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