The invention relates to a method for the aerodynamic stabilisation of a spacecraft during re-entry, for the recovery thereof, said craft comprising a long body (1), such as an axisymmetrical or quasi-axisymmetrical body. The invention is characterised in that the method consists in deploying an inflatable structure (2, 20) which has an axis that coincides with the longitudinal axis of the body (1) and which is disposed between the nominal centre of gravity and the rear end of the body, said structure being dimensioned such as to draw the centres of thrust and gravity closer together and, in this way, to maintain the body (1) in an equilibrium incidence range during the descent of the craft into the atmosphere.
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