METHOD FOR DETERMINATION OF AERODYNAMIC CHARACTERISTICS OF GUIDED MISSILE IN FLIGHT, METHOD FOR DETERMINATION OF ANGLE OF ATTACK OF MISSILE IN FLIGHT, METHOD FOR DETERMINATION OF MISSILE ATTITUDE AND DEVICES FOR THEIR REALIZATION Russian patent published in 2003 - IPC

FIELD: rocketry, applicable at flight tests of missiles and rockets for determination of their aerodynamic characteristics in flight. SUBSTANCE: the method for determination of the aerodynamic characteristics based on telemeter transmission of signals of the aerodynamic control surface angle transducer and roll-angle pick-off consists in the fact that that before the launch of the guided missile the effect of the aerodynamic load of the control surfaces is simulated, and the function of sensitivity of the control actuator dynamic parameter to the value of aerodynamic load of the control surfaces is experimentally determined. In the process of flight of the guided missile the value of the dynamic parameter of the control actuator is successively determined by the signal of the aerodynamic control surface angle transducer and the value of the aerodynamic load with respect to the sensitivity function corresponding to this value. Using a definite mathematical relation the functions of variation of the angle of attack and the derivative of the aerodynamic coefficient of the hinge moment of the control surfaces with respect to the effective angle of their deflection in the missile flight trajectory are calculated. In other points of the formula the peculiarities concerning the determination of the angle of attack, stabilization of the missile attitude are revealed, and the principal diagram of the radiotelemetry and computer units, is revealed. EFFECT: provided determination of the coordinate of the missile attitude in flight without additional metering devices. 6 cl, 3 dwg