PROCEDURE ESTABLISHING LIMITS OF RANGE OF POSSIBLE LAUNCH OF ROCKET

摘要

FIELD: determination of limits of range of feasible launch of aircraft guided rocket. SUBSTANCE: with given collection of launch conditions, specified law of target motion and preset characteristics of aircraft guided rocket process of guidance of aircraft guided rocket is divided into stages. At each stage change of modulus of velocity vector of aircraft guided rocket is set in the form of linear function which parameters and parameters of motion of aircraft guided rocket with reference to target are established by analytical expressions obtained as result of solving of differential equations for modulus of velocity vector and rate of closure of aircraft guided rocket with target along trajectory on which coupling superimposed on motion of aircraft guided rocket by process of guidance and conditions ensuring uninterrupted guidance of aircraft guided rocket and operation of fuze are provided. Limits of range of possible launch are established by summation of increments of range between aircraft guided rocket and target at each stage with allowance for operation range of control system of aircraft guided rocket. Procedure makes it possible to diminish operation time of digital computer in process of determination of limits of range of possible launch by factor of 1000 as compared with other existing procedures and error in establishment of these limits does not exceed 5% of their precise values. EFFECT: diminished operation time of digital computer while determining limits of range of possible launch of aircraft guided rocket with sufficiently high precision in wide range of measurement of launch conditions of aircraft guided rocket. 2 dwg