Countermeasure decoy system intended to be mounted on an aircraft

Counter-measure decoy system designed to be installed on an aircraft comprising:

• counter-measure projectiles (6);
• at least one tube (5) for receiving said counter-measure projectiles in series and for successive controllable launching of said counter-measure projectiles;
• and
• a control mechanism (7) for advancing said projectiles inside said tube, wherein:
• said counter-measure projectiles (6) respectively comprise dimensionally identical external cylindrical bodies (80), housed inside said tube and each having a deployable-tail-fin aerodynamic stabilisation device (9), which tail-fins assume a folded position inside the body when said counter-measure projectiles are inside said tube, and a deployed position outside of said tube, and
• said system comprises a projectile ejection module (8), with an axial passage (12), fixedly arranged as an extension of said tube, opposite said control mechanism, and successively containing, after said control mechanism, said counter-measure projectiles (6) to be ejected from said tube by a controllable ejection device (25) connected to said module,
• wherein each of said counter-measure projectiles (6) with external cylindrical bodies are mounted in respective, identical support cradles (20), which are housed inside said tube and laterally open, and said ejection module (8) with an axial passage (12) for receiving said cradle which carries said associated counter-measure projectile has a lateral opening (11) through which said counter-measure projectile is ejected from its cradle by said ejection device (25).

Counter-measure decoy system designed to be installed on an aircraft comprising:

• counter-measure projectiles (6);
• at least one tube (5) for receiving said counter-measure projectiles in series and for successive controllable launching of said counter-measure projectiles;
• and
• a control mechanism (7) for advancing said projectiles inside said tube, wherein:
• said counter-measure projectiles (6) respectively comprise dimensionally identical external cylindrical bodies (80), housed inside said tube and each having a deployable-tail-fin aerodynamic stabilisation device (9), which tail-fins assume a folded position inside the body when said counter-measure projectiles are inside said tube, and a deployed position outside of said tube, and
• said system comprises a projectile ejection module (8), with an axial passage (12), fixedly arranged as an extension of said tube, opposite said control mechanism, and successively containing, after said control mechanism, said counter-measure projectiles (6) to be ejected from said tube by a controllable ejection device (25) connected to said module, wherein said deployable tail-fins (9) of said counter-measure projectiles are in the form of at least two vanes, and
• wherein said vanes (9) are housed inside lateral slots (53) of said cylindrical body (80) and are held in a folded position inside said cradle by a rotary ring (54) connected to said body and surrounding said tail-fin vanes and, following the ejection of one of said counter-measure projectiles and under the action of a resilient element (57), said ring rotates in order to locate its lateral openings (56) opposite said slots (53) and to cause said tail-fins to move from the folded position to the deployed position.