FIELD: transport.
SUBSTANCE: invention relates to aerospace engineering. Proposed method consists in performing attitude maneuver according to pre-entered rocket control program. Prior to launching the rocket, horizontal wind speed and direction at launching site are measured. Program dependencies of pitch and yaw angle variations are calculated that, with due allowance for wind effects, to allow desirable direction of rocket engine jet traces position on horizontal plane of launching table. Calculated program dependencies are entered into flight mission. After rocket launching, rocket angular position is stabilised along pitch and yaw angles relative to program magnitudes by deflecting rocket engine swinging chambers starting from authorised minimum height till maximum flight height whereat engine jet effects do not display.
EFFECT: simplified launching structures, longer life.
8 dwg
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