FIELD: comprehensive monitoring of flying vehicle control systems. SUBSTANCE: proposed method and design provide for in-flight determination of degree and direction if center-of-mass shift due to inadherence to loading rules, spontaneous displacement of cargo, fuel system failure, or unbalanced fuel supply from tanks, and also for adequate control of rudder deflection to compensate for impact of this shift. Method and device are aimed at determination of interrelation between increment of absolute linear acceleration of flying vehicle at its arbitrary point relative to its center-of-mass acceleration and degree and direction of shift of this point from center of mass in the course of flight. Proposed method is implemented by means of accelerometer, gravimeter, angular velocity sensor, adder, two frequency selectors, and center-of- mass current coordinate unit, all these devices being interconnected. EFFECT: provision for ensuring stability of flying vehicles under conditions of external and internal disturbing impacts. 20 cl, 18 dwg
