MISSILE CONTROL METHOD AND CONTROL SYSTEM FOR ITS IMPLEMENTATION Russian patent published in 2014 - IPC F41G7/00 

FIELD: weapons and ammunition.

SUBSTANCE: invention refers to the field of development of missile guidance systems and may be used in antitank guided missile and ground-to-air missile systems. The essence of the proposed totality of technical solutions consists in improving the accuracy of the rudders drive operation by decreasing its "non-zero". The essence of the proposed totality of technical solutions consists in the following: a signal controlling self-oscillating drive is additionally introduced by a summing up signal proportional to its integrated value, which minimises the "non-zero" in a closed system embraced by a negative backlink. A method of a missile control includes formation of a control signal of the self-oscillating drive of aerodynamic rudders by the missile control system, this signal linearisation by oscillation by means of this signal summing up with an external linearising signal and corresponding deflection by the aerodynamic rudders drive. The new is that the signal proportional to the integrated vibrational-linearised signal is formed, and the signal controlling self-oscillating drive is formed as a sum of the vibrational-linearised signal and the signal proportional to the integrated vibrational-linearised signal. At that an integration factor k_i, 1/s is determined according to expression $$\frac{20\dots 30}{t_f}<k_i<\frac{{\omega }_{\text{dtr}}}{20\dots 30},$$ where t_f - firing-to-impact time to the maximum firing range, s; ω_dtr - drive transmission region, 1/s. In the missile control system implementing this method, containing a series-connected device for measurement of a missile misalignment with the preset guide line and a device for control signals formation, as well as a generator of linearising oscillations and the aerodynamic rudders drive, containing a series-connected power amplifier, a relay element, a steering actuator, a rudders deviation sensor and a summing-up amplifier, which second input is connected to the missile control equipment output, which is a control signals formation device output, the new is that in it introduced are a series-connected integrating amplifier and the second summing-up amplifier, which output is connected to the power amplifier input, at that an input of the integrating amplifier and the second input of the second summing-up amplifier are connected to the output of the first summing-up amplifier, and the output of the linearising oscillations generator is connected to the third input of the first summing-up amplifier.

EFFECT: improving guidance accuracy of missiles with aerodynamic rudders.

2 cl, 3 dwg