Abstract: The invention concerns a device comprising elastic stress-absorbing means for installed between first (10) and second (11) rigid annular members centered on the launch vehicle longitudinal axis and integral with the launch vehicle (1) and the payload (4) respectively, and device for controlling the elastic stress-absorbing devices capable of adapting the device rigidity to the different phases of the launching vehicle flight. The invention is characterized in that the control device comprise at least a plurality of hydraulic stops (13j) each arranged between the first (10) and second (11) rigid annular members, the stops (13j) being mobile at least between a first position wherein the rigidly link the annular members (10, 11) and a second position wherein the elastic stress-absorbing devices are activated.

Abstract: The invention concerns a launch vehicle comprising a shroud (1a, 5a) supporting auxiliary propellers (2, 3) applying in operation excess flow of stresses to the shroud (1a, 5a), said device comprising means for coupling the payload (4) with the launch vehicle shroud. The invention is characterized in that the coupling means are designed to ensure a mechanical coupling between the payload (4) and the shroud along the direction of the launch vehicle longitudinal axis (X), and to cause them to be disengaged along radial and tangential directions. The invention is useful for neutralizing the effects on the payload of excess stresses applied on the launch vehicle shroud by the auxiliary propellers (2, 3).