GUIDANCE METHOD TO OPTIC BEAM OF MISSILE LAUNCHING FROM MOBILE CARRIER, AND GUIDANCE SYSTEM FOR ITS IMPLEMENTATION Russian patent published in 2011 - IPC F41G7/26 

FIELD: weapons and ammunition.

SUBSTANCE: method involves formation of two beams in the form of sequence of short light pulses projected in the form of strips of constant width, which are perpendicular to each other, subsequent orthogonal scanning of beams as to heading and pitch relative to strip length, transmission to the missile of information on spatial position of beam and generation of guidance command in missile equipment. In addition, variation of carrier roll angle α is measured after missile launching; components of coordinates Y_b·cos(α) and Y_b·sin(α) of the beam scanned as to pitch and Z_b·cos(α) and Z_b·sin(α) of the beam scanned as to heading are determined and transmitted to missile in sequence of light pulses, and its coordinates are determined in missile equipment as per the following ratios: Z_m=Z_b·cos(α)+Y_b·sin(α), Y_m=Y_b·cos(α)-Z_b·sin(α), where Z_m, Y_m - current missile coordinates. To the carrier equipment there introduced is in-series connected roll angle sensor of carrier and sine-cosine functional converter, as well as product unit. The first and the second summation units are added to the missile equipment.

EFFECT: improving guidance accuracy and maintaining stability of missile control circuit due to compensation of turn of coordinate system of movable carrier relative to missile coordinate system after its launching.

2 cl, 6 dwg