METHOD FOR GUIDING REMOTELY CONTROLLED MISSILE AND GUIDING SYSTEM FOR REALIZATION OF SAID MISSILE Russian patent published in 2005 - IPC

FIELD: rocketry.

SUBSTANCE: method includes measuring coordinates of target and missile, forming angular displacement of kinematic trajectory of guiding of missile relatively to target tracking line in vertical and sloped guiding planes missile control commands are formed, proportional to angular error between coordinates of missile and target tracking line with consideration of angular displacement of kinematic trajectory of missile, and control commands are sent to missile. In each plane of missile movement trajectory model of mating of missile coordinates and target coordinates is formed in form of polynomials of appropriate missile coordinates in function of time remaining before meeting of missile and target. In current time coordinates of meeting point are predicted and time, remaining before that, is formed for each movement plane appropriately to current time coordinates of missile, coordinates of predicted meeting point and values of required angles of meeting of missile with target, and limiting conditions are also predicted for mating trajectory model of missile and target coordinates. With consideration of formed limiting conditions parameters of mating trajectory model are determined, coordinates of coordinates mating trajectory are transformed to coordinates of angular displacement of kinematic trajectory of missile relatively to target tracking line in each guiding plane. Then missile is guided with consideration of received angular deviation of kinematic trajectory of missile relatively to target tracking line.

EFFECT: secured required contact angle of missile and target.

2 cl, 1 dwg