FIELD: engines and pumps.
SUBSTANCE: in steady-state flight mode of flying laboratory (HFL), at which the sum of longitudinal aerodynamic moment and moment from engine traction force is equal to zero, pulse stepped deviation of altitude control through δpulse angle is set additionally, angles of deflections of altitude control and torque moments are measured in excited motion, and increment of aerodynamic moment, which is determined only with control deflection relative to its balancing value at pulse supply, is calculated. Then, as per measurement results obtained during flight tests, there calculated is derivative as per deviation angle of altitude control from aerodynamic moment coefficient; after supply of pulse there measured are current values of velocity pressure, deviation angle of altitude control and there determined is turning angle φ of thrust vector P"двт".
EFFECT: improving the accuracy of determining the turning angle of thrust vector owing to additional measurements of parameters during short-period movement of flying laboratory around centre of mass.
3 dwg
