Patent RU-2659622-C1 (RU)
Inventor: GUSEV ANDREJ VIKTOROVICH
IPC: F41G7/00
Filed: 2017-08-29
Granted: 2018-07-03
Abstract: FIELD: rocket equipment. 
     SUBSTANCE: invention relates to the control systems, in particular to rocket equipment with homing heads, and can be used in guided weapon systems located on the aerial delivery vehicles. In the rotating along the roll angle with direction gyroscope to the target acquisition zone by the homing head rocket outputting method, including the transport-launch container orientation before the missile launching relative to the target line of sight at given angles ϕ H , θ H , uncaging the direction gyroscope before the missile lift-off, missile longitudinal axis deviations on the yaw and pitch angles measurement relative to the memorized in the moment of its position direction gyroscope uncaging during the missile flight and the control commands generation to the actuator in proportion to the measured angular deviations before the target acquisition by the homing head, in addition, during the missile launching preparation process, measuring the carrier roll angle and the target line of sight angles relative to the associated with the carrier coordinates system, and at the time of the direction gyroscope uncaging, memorizing the carrier roll angle γ H0  and the target line of sight angles ϕ Y0 , ϕ Z0 , calculating the transport-launch container orientation errors relative to the predetermined direction, generating the transport-launch container orientation errors correction signals U Δθ , U Δϕ  and command of the missile programmed turn in the vertical plane and summarizing them with the missile measured deviations by the yaw and pitch angles. To implement the method, introduced are memory device, by its five inputs connected to the corresponding on-board digital computer five outputs, the first and second functional converters, which inputs are connected to the memory device first and second outputs, respectively, phase shifter, which first and second inputs are connected to the first and second functional converters outputs, respectively, phase shifter third input is connected to the on-board digital computer sixth output, and the phase shifter first and second outputs are connected to the commands generation unit fourth and fifth inputs, respectively, which first, second and third outputs are connected to the commands generator sixth, seventh and eighth inputs, respectively, in-series connected gyro-coordinator with the roll angle sensor and the modulation signals generator, which first and second outputs are connected to the actuator third and fourth inputs, respectively, and to the control commands generator ninth and tenth inputs, respectively, which eleventh input is connected to the direction gyroscope second output, and the control commands generator third and fourth outputs are connected to the homing head first and second inputs, respectively. 
     EFFECT: increase in the reliability based on the targets hitting increased probability with ensuring the missiles with the direction gyroscope output to the located at long ranges targets emission homing head acquisition zone high accuracy, due to the transport-launch container relative to the target line of sight orientation errors calculation and their subsequent compensation. 
     3 cl, 3 dwg