Orientable rocket-motor system

An orientable rocket motor system for an airborne vehicle, comprising:

• a rocket motor comprising a combustion chamber connected by a nozzle neck to a nozzle having a gas-ejection orifice;
• and
• a framework that supports said rocket motor in a reference position defining a reference axis, said reference axis being orthogonal to said gas-ejection orifice of the nozzle and passing through the center of said gas-ejection orifice when said rocket motor is in said reference position,
• wherein said framework is coupled to said rocket motor at a part of said nozzle adjacent to said nozzle neck, said framework comprising articulatedly connected support members configured to tilt said rocket motor nozzle and said combustion chamber so that said rocket motor adopts, with respect to said reference position, a number of tilted positions in which the center of said gas-ejection orifice of the nozzle is situated on said reference axis.