FIELD: aviation; astronautics.;SUBSTANCE: invention relates to a method of aerospace launching of small artificial Earth satellites (AES) to near-earth orbit. In order to implement the trajectory of the carrier aircraft at the stage connection points, the correction sections are included: steady-state sections in the preset mode, duration of which can be compensated for deviations from flight program at previous stages. During pre-launch maneuver for compensation of deviations from the program based on the preliminary calculation of the missile launch trajectory there is a minimum value of the horizontal component of the missile (W) speed, sufficient to bring artificial Earth satellite to given orbit, which defines start-up window. Missile launching is performed if current moment of time is within start-up window: pre-launch maneuver is carried out, including acceleration to M=2.0, set of altitude with maximum thrust corresponding to forced mode, transition to climb mode with preset overload value and launch of missile.;EFFECT: technical result is providing optimum conditions for rocket launching with AES.;1 cl, 4 dwg
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