AERODYNAMIC STABILIZER OF ROCKET PROJECTILE FOR SALVO FIRING

摘要

FIELD: rocket engineering. SUBSTANCE: invention is related to aerodynamic stabilizer and can be used to design rocket projectiles of salvo firing systems with separated war heads. Fairing of aerodynamic stabilizer has L-shaped grooves. One section of grooves is oriented in axial direction and the other one is oriented to side opposite to direction of rotation of projectile to form obtuse angle. Fairing from inside and blade on side of war head are fitted with rests between which springs manufactured in the form of compression springs are placed. Invention makes it feasible to design stabilizer ensuring high efficiency and reliability of combat employment thanks to prevent of collision of jet engine and war head after their separation. EFFECT: high efficiency and reliability of combat employment of rocket projectiles. 2 dwg