FIELD: rocketry and space engineering; vertical landing and take-off from celestial bodies having hard, liquid or dust-like surface. SUBSTANCE: according to invention, spacecraft includes take-off and landing stages arranged in tandem, engine plants with main engines of take-off stage installed in its central portion whose axis of symmetry passes through center of mass of take-off stage and external tanks of landing stage which are secured on its load-bearing frame. Load-bearing frame has circular form with center located on longitudinal axis of symmetry of main engines of take-off stage. External propellant tanks are articulated over periphery of this circular load-bearing frame for turn through angle of no less than 90 deg. EFFECT: enhanced reliability of spacecraft; reduced risk under extremal conditions. 2 cl, 2 dwg
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