REMOTELY CONTROLLED MISSILE GUIDANCE METHOD

FIELD: rocket technology.SUBSTANCE: invention relates to rocket engineering and can be used in guidance systems of guided missiles. Method comprises measuring the target and missile coordinates, forming the current parameters of the missile's movement relative to the target, forming missile control signals in accordance with the parameters of the missile's movement relative to the target, transmission of control signals to the missile and guidance of the missile on the generated control signals. Method includes converting target and missile coordinates into rectangular coordinates, estimating the current parameters of target and missile movement, forming the current parameters relative to missile movement according to estimated parameters of target and missile movement, determining the current time remaining until the missile meets the target, forming the signals of the current angular velocity of the missile-target sight line according to the parameters relative to missile movement, determining the signals of the current miss proportionally to the signals of the angular velocity of the sight line, determining the estimates of the current miss, predicting the miss signals at the meeting point, according to the estimates of the current miss, taking into account the time remaining until the missile meets the target, forming signals of the current angular velocity of the missile-target sight line of at the meeting point, generating signals of the program current offset of the angular velocity of the sight line and further generating missile control signals in proportion to the signals of the angular velocity of the sight line at the meeting point, taking into account the signals of the program offset of the angular velocity of the missile-target sight line.EFFECT: technical result is reduced required overload of the missile, dynamic guidance error ensuring the required angles of the meeting of the missile with the target and expanded conditions for use of the remote control missile.2 cl, 1 dwg Изобретение относится к ракетной технике и может быть использовано в системах наведения телеуправляемых ракет. Технический результат - снижение потребной перегрузки ракеты, динамической ошибки наведения с обеспечением требуемых углов встречи ракеты с целью и расширение условий применения телеуправляемой ракеты. Для этого осуществляют измерение координат цели и ракеты, формирование текущих параметров движения ракеты относительно цели, формирование сигналов управления рак