| 摘要 |
FIELD: missile guidance systems, applicable in anti-tank and anti-aircraft missile systems. ^ SUBSTANCE: according to the invention, forming of modulated radiation on the launcher, reception of the radiation on the missile and generation of control signals in the vertical and horizontal planes, modulation of these signals by signals periodic in missile roll angle are accomplished. Linearization signal, cophased with the signals periodic in roll angle, are formed on condition n=3, with n=omega0/gamma where omega0 - the frequency of the linearization signals, gamma - spinning speed of missile in rolling. The modulated control signals and the linearization signal are summed up. Forming of the relay two-position signal is performed by determination of the sign of this sum and transduction of the obtained relay control signal to the deflection of the control actuator. The linearization signal up to the moment of the missile sustainer engine starting and after its starting is formed on condition n=3, and during operation of the sustainer engine - on condition n=2. ^ EFFECT: enhanced guidance accuracy in all legs of the flight characterized by dispersion of the missile and control actuator ballistic and dynamic characteristics. ^ 2 cl, 6 dwg |
