초록 ▼

In order to allow decoy projectiles (6) to be launched with optimal quality of flight, the projectiles respectively include external cylindrical bodies (80) which are dimensionally identical, housed in the tube and each having a deployable-fins (9) aerodynamic stabilization device, that adopt a fold

In order to allow decoy projectiles (6) to be launched with optimal quality of flight, the projectiles respectively include external cylindrical bodies (80) which are dimensionally identical, housed in the tube and each having a deployable-fins (9) aerodynamic stabilization device, that adopt a folded position inside the body when the projectile is in the tube, and a deployed position outside of the tube. To achieve that, the system includes a projectile ejection system (8), with an axial passage (12), arranged fixedly as a continuation of the tube, at the opposite end to the advance mechanism, and containing, in succession, after the control mechanism, the projectile (6) that is to be ejected by a controllable ejection device (25) connected to the module.

대표청구항 ▼

1. Counter-measure decoy system designed to be installed on an aircraft comprising: counter-measure projectiles (6);at least one tube (5) receiving said counter-measure projectiles in series and for successive controllable launching of said counter-measure projectiles; anda control mechanism (7) for

1. Counter-measure decoy system designed to be installed on an aircraft comprising: counter-measure projectiles (6);at least one tube (5) receiving said counter-measure projectiles in series and for successive controllable launching of said counter-measure projectiles; anda 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 stabilization 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,said system comprises a projectile ejection module (8), with an axial passage (12), fixedly arranged in 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 the counter-measure projectiles (6) are ejected through a lateral opening (11) in said module (8). 2. System according to claim 1, wherein said counter-measure projectiles (6) with cylindrical bodies (80) housed inside said tube and said module have counter-measure devices (81) that are identical or different for at least two of said projectiles. 3. System according to claim 1 wherein a counter-measure device (81) of at least one of said counter-measure projectiles is an active electromagnetic counter-measure device. 4. System according to claim 1, wherein a counter-measure device (81) of at least one of said counter-measure projectiles is an infrared counter-measure device. 5. System according to claim 1, wherein at least one of said counter-measure projectiles (6) is equipped with a propulsion unit (82) housed inside said body. 6. System according to claim 1, wherein said tube (5) is at least arranged approximately parallel to the longitudinal axis of the aircraft. 7. System according to claim 1, wherein each of the counter-measure projectiles (6) is mounted in a respective support cradle, wherein each of said counter-measure projectiles is ejected from a lateral opening in said respective support cradle by the controllable ejection device. 8. System according to claim 1, wherein the deployable-tail-fin aerodynamic stabilisation device (9) of each counter-measure projectiles faces the projectile ejection module (8) and a front of each counter-measure projectile faces said control mechanism. 9. System according to claim 1, 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 an associated counter-measure projectile has a lateral opening (11) through which said counter-measure projectiles are ejected from its cradle by said ejection device (25). 10. System according to claim 9, wherein in addition to the relevant counter-measure device (81) and the deployable tail-fins (9) downstream of said body, a chamber (34) associated with said device (25) for ejecting from said cradle, a locking mechanism (35) between said body and said cradle and an electrical connector (62, 63) for firing orders and other operating data are located inside said cylindrical body (80) common to each projectile. 11. System according to claim 9, wherein said device (25) for ejecting each counter-measure projectile is of a pyrotechnic type and is arranged in either the cradle or the counter measure projectiles in order to radially eject said projectiles through said lateral opening (11) of said module (8). 12. System according to claim 9, wherein that position retention means are provided between said cradle (20) and said ejection module (8), with axial and transverse immobilisation of said cradle in relation to said module. 13. System according to claim 12, 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. 14. System according to claim 1, wherein said deployable tail-fins (9) of said counter-measure projectiles are in the form of at least two vanes. 15. 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; anda 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, andsaid 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). 16. System according to claim 15, wherein in addition to respective counter-measure devices (81) and the deployable tail-fins (9) downstream of said body, a chamber (34) associated with said controllable ejection device (25) for ejecting from said cradle, a locking mechanism (35) between said body and said cradle of one of said counter-measure projectiles and an electrical connector (62, 63) for the firing orders and other operating data are located inside said cylindrical body (80) common to each projectile. 17. System according to claim 15, wherein said controllable ejection device (25) for ejecting each counter-measure projectile is a pyrotechnic ejection device and is arranged in either the cradle or the counter-measure projectile in order to radially eject said projectile through said lateral opening (11) of said module (8). 18. 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; anda 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, andsaid 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, andwherein 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. 19. System according to claim 15, wherein position retention means are provided between said cradle (20) and said ejection module (8), with axial and transverse immobilisation of said cradle in relation to said module.