ANTI-AIRCRAFT GUIDED MISSILE 9M96

FIELD: weapons.SUBSTANCE: invention relates to the field of military equipment, namely to missiles with a gas-dynamic control system, and can be used in the development of guided missiles, anti-missiles and ballistic missiles. Missile comprises body (1) accommodating power supply system, combat equipment, control system hardware, cruise propulsion system and transverse control propulsion system (3). Transverse control propulsion system (3) consists of a gas generator connected to nozzles (4) located in the equatorial plane of the rocket in the centre of its mass (2). Nozzles (4) are closed by covers, which have independent opening. Control system provides transverse thrust effect on rocket of design value due to simultaneous opening of two nozzles of propulsion system of transverse control (3), which total thrust is directed along bisector of angle between axes of connected nozzles and is proportional to double cosine of half of angle between axes of connected nozzles. When the preset transverse displacement of the missile is achieved to compensate for the miss relative to the target, the control system provides the creation of the opposite thrust of the propulsion system due to simultaneous opening of nozzles of propulsion system of transverse control (3), opposite to previously opened nozzles, total thrust of which compensates thrust of previously opened nozzles.EFFECT: controllable change in the trajectory of movement of the centre of mass of the missile is provided without changing the angular position of the construction axis of the missile in pitch and heading, which improves the dynamics of the missile, reduces fuel consumption, makes it possible to use rocket fuel with limiting value of specific impulse in transverse control propulsion system.1 cl, 1 dwg Изобретение относится к области военной техники, а именно ракетам с газодинамической системой управления, и может быть использовано при разработке управляемых ракет, противоракет и баллистических ракет. Ракета содержит корпус (1), размещенные в нем систему энергопитания, боевое снаряжение, аппаратуру системы управления, маршевую двигательную установку и двигательную установку поперечного управления (3). Двигательная установка поперечного управления (3) состоит из газогенератора, соединенного с соплами (4), размещенными в экваториальной плоскости ракеты в центре ее масс (2). Сопла (4) закрыты крышками, которые имеют независимое открытие. Система управления обеспечивает поперечное тяговое воздействие