FIELD: rocketry and space engineering; operation of liquid-propellant engine plant for descent of spacecraft on Earth or another atmosphere planet. SUBSTANCE: proposed method includes acceleration of propellant, temporary delay for separation of gas bubbles and discharge of separated gas beyond spacecraft making use of descent g-load at the beginning of aerodynamic braking of spacecraft in atmosphere of planet; spacecraft is so oriented that direction of vector of main aerodynamic force acting of spacecraft coincides with direction from liquid cavity of intake along intake axis; discharge of gas is effected through control engines of this plant which create similar moment in opposite directions during orientation within period of time determined as ratio of gas mass in liquid cavity of tank to total flow rate of gas through control engines. EFFECT: low cost of method; enhanced reliability. 2 cl, 3 dwg
