The invention discloses a carrier
rocket first-
level flight section aerodynamic parameter identification method and related equipment, and relates to the field of carrier rockets, and the method comprises the steps: calculating an
attack angle and a sideslip angle of a
rocket first-
level flight section according to actually measured
wind field data and flight
telemetry data of the launching day; obtaining
angular acceleration information according to
angular velocity information in the flight
telemetry data; calculating the
resultant moment information of the
rocket body according to the
angular acceleration information and the rotational
inertia of the rocket body; according to the rocket body
resultant moment information, the
dynamic pressure information and the rocket
body size information, rocket body moment coefficient information is calculated, and the rocket
body size information comprises rocket body reference area information and rocket body length information; reverse interpolation operation is carried out according to known aerodynamic parameters and the
aerodynamic torque coefficient to obtain
rudder deflection control quantities, the known aerodynamic parameters comprise the
attack angle, the sideslip angle and the Mach number, and the
rudder deflection control quantities comprise the pitching
rudder deflection control quantity, the yawing rudder deflection control quantity and the rolling rudder deflection control quantity; and comparing the rudder deviation control quantity with the rudder deviation during actual flight to judge aerodynamic parameters.