A.S. Ermolaev - Part-programming Engineer, JSC «MKB «Fakel» (Moscow, Himki). E-mail: e06@inbox.ru

A heuristic approach of control algorithm synthesis for anti-aircraft missile is considering. The purpose of construction of the new control algorithm is to create an autopilot structure that allows expanding far boundary of in-tercept zone. It-s necessary to guarantee that the terminate missile speed at intercept point will be above the minimum value based on requirements of stabilized flight. Estimation of algorithm effectiveness in far boundary of intercept zone is based on the maximum speed criteria at intercept point. Existing control algorithms can be divided into methods that follow reference trajectory and methods in which the control commands are based on current state of missile and target. Presented in the article algorithm belongs to second type. The control commands calculation is based on the current parameters of relative motion and consider the rational use of kinetic energy that has effect on terminate speed and available lateral acceleration at intercept point. The algorithm requires splitting trajectory path into stages. Each stage has specific control structure. The base stages are: climb, gliding with angle of attack of maximum aerodynamic quality with further decreasing command, ballistic flight into predicted intercept point, and homing with proportional guidance law. Proposed structure is aimed to ensure: integral energy efficiency of guidance; low sensitivity to random changes in intercept point coordinates; resistance to various kinds of disturbances; implementation in real time onboard computers.

 

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