# US 2014/0196597 A1 · Countermeasure decoy system intended to be mounted on an aircraft > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2014/0196597 A1 - Document ID: US20140196597A1 - Status: Published application - Kind: A1 - Application number: 14/131,843 - Filed: 2012-07-09 - Published: 2014-07-17 - Earliest claimed: 2011-07-12 - Assignees: Mbda France - Inventors: David Le Croller; Jean-Luc Assouly - Web page: https://patentgrep.com/patent/US20140196597A1 ## CPC - B64D 1/02: Dropping, ejecting, or releasing articles (jettisonable fuel reservoirs B64D37/12) - F41A 9/72: Tubular magazines, i.e. magazines containing the ammunition in lengthwise tandem sequence - F41F 3/06: from aircraft {(F41F3/0406 takes precedence; arrangements of rocket launchers on aircraft B64D7/08; bomb releasing in flight B64D1/06)} - F41F 5/00: Launching-apparatus for gravity-propelled missiles or projectiles (from aircraft B64D1/04) - F41F 7/00: Launching-apparatus for projecting missiles or projectiles otherwise than from barrels, {e.g. using spigots}(F41F3/04 takes precedence; {centrifugal sling apparatus F41B3/04}) - F42B 12/70: for dispensing radar chaff or infrared material (radar-reflector targets, active targets transmitting infrared radiation F41J2/00; radar-reflecting surfaces H01Q15/14) - B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT - F41A: FUNCTIONAL FEATURES OR DETAILS COMMON TO BOTH SMALLARMS AND ORDNANCE, e.g. CANNONS; MOUNTINGS FOR SMALLARMS OR ORDNANCE - F41F: APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS (smallarms F41C); LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS (functional features or details common to both smallarms and ordnance, mountings therefor F41A; projecting missiles without use of explosive or combustible propellant charge F41B) - F42B: EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION (explosive compositions C06B; fuzes F42C; blasting F42D) ## Abstract In order to allow decoy projectiles (6) to be launched with optimal quality of flight, the projectiles respectively comprise external cylindrical bodies (80) which are dimensionally identical, housed in said 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, said system comprises a projectile ejection system (8), with axial passage (12), arranged fixedly in the 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 said module. ## Claims ### Claim 1 Counter-measure decoy system designed to be installed on an aircraft and of the type comprising: counter-measure projectiles (6); at least one tube (5) for receiving said counter-measure projectiles in series and for the successive controllable launch of said 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 projectile is 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 in the extension of said tube, opposite said advance mechanism, and successively containing, after said control mechanism, said projectile (6) to be ejected from said tube by a controllable ejection device (25) connected to said module. ### Claim 2 (depends on 1) System according to claim 1, wherein said 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. ### Claim 3 (depends on 1) System according to claim 1 wherein said counter-measure device (81) of at least one of said projectiles is of the active electromagnetic type. ### Claim 4 (depends on 1) System according to claim 1, wherein said counter-measure device (81) of at least one of said projectiles is of the infrared type. ### Claim 5 (depends on 1) System according to claim 1, wherein said projectile (6) is equipped with a propulsion unit (82) housed inside said body. ### Claim 6 (depends on 1) System according to claim 1, wherein said tube (5) is at least arranged approximately parallel to the longitudinal axis of the aircraft. ### Claim 7 (depends on 1) System according to claim 1, wherein said 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 projectile has a lateral opening (11) through which said projectile is ejected from its cradle by said ejection device (25). ### Claim 8 (depends on 7) System according to claim 7, 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 the firing orders and other operating data are located inside said cylindrical body (80) common to each projectile. ### Claim 9 (depends on 7) System according to claim 7, wherein said device (25) for ejecting each projectile is of the pyrotechnic type and is arranged in either the cradle or the projectile in order to radially eject said projectile through said lateral opening (11) of said module (8). ### Claim 10 (depends on 1) System according to claim 1, wherein said deployable tail-fins (9) of said projectile are in the form of at least two vanes. ### Claim 11 (depends on 10) System according to claim 10, 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 said projectile 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. ### Claim 12 (depends on 7) System according to claim 7, 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.