MISSILE CONTROL METHOD AND CONTROL SYSTEM THEREFOR Russian patent published in 2015 - IPC F41G7/00 

FIELD: physics, navigation.

SUBSTANCE: disclosed group of engineering solutions relates to a class of radiation techniques and missile control systems which facilitate direct hit of a target. The disclosed missile control method includes generating an electromagnetic beam, encoding the cross-section of the beam or control field with electromagnetic pulses, the intensity and duration of each pair of which is constant on any circle concentric with respect to the centre of the beam and linearly varies from the centre of the beam to the periphery, measuring, by the receiving device of the missile, the current values thereof and converting into an electrical signal which is proportional to the deviation of the receiving device of the missile from the centre of the control field, measuring the angular position of the receiving device of the missile relative to the radius vector connecting the centre of mass of the missile and the centre of the control field, generating a control signal, deviating the steering apparatus, generating a control force proportional to the deviation of the steering apparatus and in accordance with the polar control law, which includes directing a polar control force towards the centre of the control field independent of the relative speed of control field and the missile, and determining the value of the generated polar control force using the relationship k_ρ=k₁(ρ+k₂ρ'+k₃ρ"), where k_ρ is the value of the polar control force, k_1,2,3 are coefficients of proportionality determined from conditions of stability and accuracy of control, ρ is the deviation of the centre of mass of the missile from the centre of the control field, ρ' is radial speed of the centre of mass of the missile, ρ" is the centripetal acceleration of the centre of mass of the missile, and varying according to the angular position of the receiving device of the missile relative to the radius vector connecting the centre of mass of the missile and the centre of the control field. The disclosed control system which carries out the disclosed missile control method comprises an electromagnetic radiation source, series-connected receiving device, coordinator, roll selection unit, control command generating unit, command conversion unit and steering gear, wherein the receiving device is shifted relative to the longitudinal axis of the missile, the roll selection unit and the command conversion unit respectively comprise series-connected narrow band-pass filter, first adder and integrator, a second adder, a multiplier; the input of the narrow band-pass filter and the second input of the first adder are connected to the output of the coordinator, the output of which is connected to the input of the integrator and the second input of the second adder, the second input of the multiplier is connected to the output of the narrow band-pass filter, and the output of the multiplier is connected to the input of the steering gear.

EFFECT: providing a missile control device with rotation of the electromagnetic information beam on the roll without compensation for "twisting" and high reliability of operation.

2 cl, 6 dwg