Missile launching and steering system

PCT No. PCT/FR95/01423 Sec. 371 Date Jun. 26, 1996 Sec. 102(e) Date Jun. 26, 1996 PCT Filed Oct. 27, 1995 PCT Pub. No. WO96/13694 PCT Pub. Date May 9, 1996This invention concerns a missile launching system, and particularly a missile launching and orientation system. It can be used to modernize miss...

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Hauptverfasser:	VLADIMIR YAKOVLEVITCH MIZROKHI, EUGENE GUEORGUEVITCH BOLOTOV, IVAN IVANOVITCH ARKHANGELSKY, VLADIMIR SERGUEEVITCH PHILIPPOV, VICTOR LEONIDOVITCH GAIDOUKEVITCH, VLADIMIR GRIGORIEVITCH SVETLOV, EUGENE AFANASSIEVITCH CHMIKOV, SERGE GRIGORIEVITCH KHITENKOV, GREGORY ANDREEVITCH STANEVSKY
Format:	Patent
Sprache:	eng
Schlagworte:	AMMUNITION APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS,e.g. CANNONS BLASTING EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION HARPOON GUNS HEATING LAUNCHERS FOR ROCKETS OR TORPEDOES LIGHTING MECHANICAL ENGINEERING WEAPONS
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Beschreibung
Zusammenfassung:	PCT No. PCT/FR95/01423 Sec. 371 Date Jun. 26, 1996 Sec. 102(e) Date Jun. 26, 1996 PCT Filed Oct. 27, 1995 PCT Pub. No. WO96/13694 PCT Pub. Date May 9, 1996This invention concerns a missile launching system, and particularly a missile launching and orientation system. It can be used to modernize missiles with an inclined launch at an angle by transforming them into missiles controlled for circular defense, avoids ejection of the passive mass within the launching area. In order to do this, the launching system comprises launching means, aerodynamic control surfaces with drive and means of orientation including at least one gas generator and nozzles connected to it. Orientation means are located in an annular body rigidly connected to the rear part of the missile body. The outside surface of the annular body is cone-shaped and is covered with a thermal insulating material forming a gas pipe, the profile of which is a continuation of the profile of the nozzle of the missile cruise engine.