RU2011154532A - GUIDANCE ON OPTICAL BEAM OF ROCKETS STARTING FROM MOBILE CARRIER - Google Patents

Abstract

1. A method for guiding an optical beam of a rocket launching from a mobile carrier, comprising forming a laser beam with a control information field on the carrier, pointing an optical sight at the target whose axis is aligned with the axis of the information field of the laser beam, orienting the axis of the launching device in the direction of the axis of the information field a laser beam, launching a rocket with folded aerodynamic rudders and entering the rocket into the information field of the laser beam, opening the radiation receiver on the rocket and generating signals, proportional to the coordinates of the rocket relative to the axis of the information field of the laser beam, and converting them into control commands, opening aerodynamic rudders, converting control commands to steering deviations, characterized in that at the time of the missile’s departure on the carrier, the angular position of the axis of the launching device relative to the carrier is measured and stored coordinate systems, as well as the angular position of the carrier relative to the earth coordinate system, the disclosure of the rudders is carried out with a time delay relative to the open When the radiation receiver is opened, the axis of the information field of the laser beam is combined with the position of the axis of the launcher stored at the moment of the launch, and at time t, which corresponds to the moment the rudders open, the axis of the information field of the laser beam begins to align with the line of sight of the target. 2 . The method according to claim 1, characterized in that the combination of the axis of the information field of the laser beam with the line of sight of the target is carried out according to the law Δφ = 0.5 · Δφ ° · [1 + cos (ω · (tt))], at t <t≤t ; Δφ = 0, for t> t, where Δφ are the current angles between

Claims (2)

1. The optical beam guidance method of a rocket launching from a movable carrier, comprising forming a laser beam with a control information field on the carrier, aiming an optical sight on the target whose axis is aligned with the axis of the laser beam information field, orienting the launch device axis in the direction of the information field axis a laser beam, launching a rocket with folded aerodynamic rudders and entering the rocket into the information field of the laser beam, opening the radiation receiver on the rocket and generating signals, proportional to the coordinates of the rocket relative to the axis of the information field of the laser beam, and converting them into control commands, opening the aerodynamic rudders, converting control commands to steering deviations, characterized in that at the time of the missile’s departure on the carrier, the angular position of the axis of the launching device relative to the carrier is measured and stored coordinate systems, as well as the angular position of the carrier relative to the earth coordinate system, the disclosure of the rudders is carried out with a time delay relative to the open When the radiation receiver is opened, the axis of the information field of the laser beam is combined with the position of the axis of the launcher memorized at the time of the rocket descent, and at time t _nv , corresponding to the moment the rudders open, the axis of the information field of the laser beam begins to align with the line of sight of the target. 2. The method according to claim 1, characterized in that the combination of the axis of the information field of the laser beam with the line of sight of the target is carried out according to the law Δφ _{wu, z} = 0.5 · Δφ ° _{wu, z} · [1 + cos (ω _{wu, z} · (tt _nv ))], for t _nv <t≤t _{kvu, z} ; Δφ _{wu, z} = 0, for t> t _{kwu, z} , where Δφ _{wu, z} are the current angles between the axis of the information field and the line of sight of the target, Δφ ° _{wu, z} are the flap angles of the axis of the information field from the line of sight of the target at the moment the radiation receiver was opened on the rocket, $${\omega }_{\mathrm{at}\mathrm{at},z}=2\cdot \frac{{\omega }_{\mathrm{at}m\mathrm{at},z}-\left|{\omega }_{0\mathrm{at},z}\right|}{\left|\Delta {\phi }_{\mathrm{at}\mathrm{at},z}^0\right|},$$

ω _{bmu, z} are the maximum angular rotational speeds of the axis of the information field in the process of combining;

at t = t _nv ,

at t = t _nv ,

,

- the angular velocity of rotation of the line of sight of the target at elevation and azimuth angles, respectively, t _{kvu, z} is the end time of the combination, t _{qy, z} = t _HB + Δt _{woo, z} , where Δt _{wu, z} = π / ω _{wu, z} .