Abstract: The present disclosure discloses a rocket braked by air recovered by turbines and a deceleration method for recovery of the same. The rocket includes a first-stage rocket and a second-stage rocket, where the first-stage rocket includes a first-stage rocket fuselage sequentially provided with a movable baffle, an oxidizer chamber, a fuel chamber, a combustion chamber, and an ejection opening from top to bottom; after the first-stage rocket is separated from the second-stage rocket, the movable baffle of the first-stage rocket is opened to generate resistance for deceleration and adjustment on a descending posture; an air inlet in a turbine is exposed at the same time, and the turbine is turned on; and after a flameout of an engine, stored compressed air is downwards ejected from the bottom of the first-stage rocket to generate thrust for deceleration, so as to achieve safe landing of the rocket.