METHOD OF INERTIAL AIRCRAFT GUIDANCE BASED ON DISCREPANCY BETWEEN DYNAMIC PROPERTIES OF TARGET AND INTERCEPTOR

摘要

FIELD: control systems.;SUBSTANCE: invention relates to control systems, in particular, to complex systems including jointly operating subsystems with different dynamic properties. Proposed guidance method allows compensating mismatch between the dynamic properties of the interceptor and the target in the guidance process without solving the complex two-point boundary problem. Control signal is generated according to law:; ;where j_i is required transverse acceleration of interceptor; – optimum estimates of courses and angular velocities of interceptor and target; and are estimates of range to target and its first derivative; T – time constant of the interceptor, which characterizes its inertia; b is control signal amplification factor; q₂₁ is the penalty rate for accuracy of guidance of the system by angle; q₂₂ is the penalty rate for accuracy of guidance of the system from angular velocity; g₂₂ is the interaction factor of the guidance and target maneuver error interaction; k is coefficient of penalties per value of control signal. In contrast to the prototype, the proposed method has a third nonstationary term which takes into account discrepancy between dynamic properties of the target and the interceptor.;EFFECT: use of the invention will make it possible to provide interception of fast-moving targets in a wide range of their speeds and courses; saving energy consumption for control at initial guidance areas and improving its accuracy at the final section.;1 cl, 8 dwg