FIELD: aerospace engineering, flight tests of new flight vehicles, or flight conditions for creation of information section of self-adaptive autopilots. SUBSTANCE: in the lengthwise passage of flight vehicle the elevator actuator is influenced simultaneously by high-frequency harmonic components of test signal. Low-frequency components provide for the necessary region of variation of the angle of attack and slip angle. High-frequency components are fed to the side channel in succession to the input of the rudder and aileron actuator, and forced motions excited by them respectively at the aileron and rudder are suppressed at rudder or elevator by a compensating signal. Parameters of motion, deflection are recorded in succession for each period of high-frequency motion in the lengthwise passage, or for their succession at low values of slip angle - in the side channel, efficiency of rudder, elevator and ailerons is determined in the form of dependences of coefficient components of the aerodynamic moment on the deflection angles of the rudder and elevator, and then dependences of coefficients of the aerodynamic moment on the angle of attack and slip angle are determined with the use of them for the whole test conditions. EFFECT: facilitated procedure. 6 dwg
