METHOD OF CRUISE MISSILE HOMING

FIELD: weapons.SUBSTANCE: invention relates to rocket engineering and can be used for development of software and hardware flight control systems, which improve combat effectiveness of using self-guided cruise missiles for various purposes. Method employs a cruise missile. It is equipped with self-guidance head - SGH, control system with on-board digital computer - OBDC, power plant with liquid fuel supply regulator, control position of fuel supply valve, aerodynamic rudders. Rocket start is started and its flight is provided to target location area. SGH is switched on and signals on characteristics of target-like objects and range to them are transmitted to OBDC. OBDC is used to calculate the flight trajectory to the target and receiving rudder control signals from the OBDC. At that, before start or during cruise missile start-up data on fuel amount in power plant tank is loaded in OBDC. During flight and before SGH connection at least once a second by the liquid fuel flow rate regulator the fuel supply valve position is fixed and data on it are transmitted to the OBDC to determine the liquid fuel flow rate and its current amount. After the SGH is switched on, the flight path to the target is calculated taking into account the current amount of fuel. At sufficient amount of fuel and at identical levels of signals from target-like objects, cruise missile is directed to one of distant targets or to the largest target with maximum effective scattering surface irrespective of range, or evasive manoeuvre is performed, or direction of approach to nearest target is changed. At insufficient amount of fuel, cruise missile is directed to nearest target.EFFECT: technical result is increase in the missile combat effectiveness during self-homing.1 cl, 1 dwg Изобретение относится к ракетной технике и может быть применено для разработки программно-аппаратных комплексов управления полетом, обеспечивающих повышение боевой эффективности применения самонаводящихся крылатых ракет различного назначения. Технический результат - повышение боевой эффективности ракеты при самонаведении. По способу применяют крылатую ракету. Ее оснащают головкой самонаведения - ГСН, системой управления с бортовой цифровой вычислительной машиной - БЦВМ, силовой установкой с регулятором подачи жидкого топлива, управляющим положением клапана подачи топлива, аэродинамическими рулями. Включают старт ракеты и обеспечивают ее полет в область расположения цели. Включают ГСН и передают в БЦВМ сигналы о хар