FIELD: control systems.SUBSTANCE: invention relates to control systems, in particular to systems that intercept priority targets (PTS), accompanied by security fighters. In the claimed method, in the filter of the goniometric channel, optimal estimates of the current airborne bearing of the target and its first derivative with respect to time, the required airborne bearing of the target are formed, and in the filter of the ranging channel, the optimal estimate of the range to the target and its first derivative with respect to time, after which, based on the formed estimates a control signal for the required lateral acceleration is generated, and in addition, at each control cycle, the phase of the quasi-harmonic component is recalculated, after which a modified control signal is generated.EFFECT: invention increases accuracy and stability of the tracking of priority targets and ensures the disruption of the guidance of its escort fighters to the interceptor missile of the priority target.1 cl, 10 dwg

Method for intercepting the priority targets with disrupting the guidance of accompanying fighters

FIELD: radio engineering; electronics.SUBSTANCE: invention relates to radio-electronic control systems (RECS) by aircraft and can be used for homing of air-to-air missile on aircraft from pair of them by its functional purpose according to the principle "master-slave". Method involves measuring and obtaining in the missile of the missile's self-guidance radar (SGR) of the angular rotation speed of the line of sight "missile-not resolved by angular coordinates of a pair of aircraft" in the horizontaland verticalplanes, measurement by means of accelerometer of own acceleration of missile in horizontal Jand vertical Jplanes, implementation in the auto-selector of the SGR speed of the missile of narrow-band Doppler filtration on the basis of the algorithm of fast Fourier transformation, generation of estimatesandtrajectories of Doppler frequencies, caused by speeds of approach of the missile with master and slave aircraft pairs, calculation of autocorrelation functions and their parameters – correlation time τand τ, natural frequency fand fautocorrelation function, root-mean-square deviation σand σfluctuations of Doppler frequency, analysis of parameters of autocorrelation functions, when conditions are met τ>τ, f f, σ>σ(6), decision is made that estimateis caused by speed of approach of missile to driven plane of pair, and estimateis caused by rate of approach of missile to master by a pair aircraft and at prelaunch TD on missile guidance on master aircraft mismatch parameters are generated in accordance with expressionsand at prelaunch TD guidance of missile on driven aircraft from pair parameters of mismatch are formed in accordance with expressionsEFFECT: broader functional capabilities on the basis of formation of mismatch parameters in the RECS with an air-to-air missile, which enable to perform a missile self-homing on an aircraft from the pair by its functional purpose according to the "master-slave".1 cl, 1 dwg

Method of forming mismatch parameters in a radio-electronic system for controlling an air-to-air missile with its self-homing on an aircraft of a pair of them according to its functional purpose on the principle of "master-slave"

FIELD: area of secondary digital processing of radar signals.SUBSTANCE: method consists in parallel tracking on the basis of narrow-band Doppler filtration and procedure of fast Fourier transformation of Doppler frequencies counts, caused by reflections of signal from fuselage of helicopter and rotary blades of rotor of helicopter. Then, the reading Fof the Doppler frequency of the spectral component with the maximum amplitude Aexceeding the first threshold Uand corresponding to the signal reflections from the helicopter fuselage is determined. Obtained discrete-successive readings of Doppler frequencies are filtered in the first tracking filter. Determining readings F, where i = 1, …, I; I is total number of amplitudes of spectral components exceeding second threshold Ucorresponding to reflections of signal from rotor blades, except for spectral component with maximum amplitude Aand corresponding reflections of signal from helicopter fuselage. Value of the second threshold Uis n times less than the value of the first threshold UCounts Fof Doppler frequency are calculated, which corresponds to energy center of signal reflections from helicopter main rotor blades, and are filtered in the second filter. In the presence of counts of Doppler frequencies of spectral components exceeding the first threshold Uand corresponding to reflections of the signal from the fuselage of the helicopter, estimates of parameters of the helicopter motion are formed when it is tracked by reflections of the signal from its fuselage. In the presence of counts of Doppler frequencies of spectral components exceeding the second threshold Uand not exceeding the first threshold U, estimates of parameters of movement of the helicopter when it is tracked by reflections of the signal from rotor blades are formed.EFFECT: providing continuous accompaniment of a helicopter in a pulse-Doppler radar station.1 cl, 2 dwg

Method of tracking a helicopter in a pulse-doppler radar station

FIELD: physics; rocket equipment.SUBSTANCE: invention relates to radio-electronic control systems (RECS) by aircraft and can be used for homing of air-to-air missile to helicopter at various nature of its flight with corresponding dynamics. Method of mismatch parameters formation in RECS with air-to-air missile at its self-homing to helicopter at various flight character, consists in the fact that in the missile radar homing (MRH) angle meter of the missile the angular velocity of rotation of the sighting line missile-helicopter is evaluated, evaluation of helicopter bearings, there determined are increments of angular rotation speeds of the line of sight missile-helicopter, caused by helicopter maneuver in horizontal and vertical planes respectively, using the accelerometer, the missile's own accelerations in the horizontal and vertical planes are measured. In the MRH auto-speed selector parallel in each optimal Kalman filter of their matrix, the helicopter is tracked along the range and Doppler frequency at various a priori data, received during filtration in each optimum Kalman filter relative to mcharacter of helicopter flight and appropriate for each flight character of jversion of flight dynamics. At that, according to the rows of the matrix of the optimal filters there are filters, in which the a priori information is the dynamic models for various hypotheses regarding the mcharacter of the helicopter flight, and on columns - filters with dynamic models for various hypotheses relative to jversions of flight dynamics of helicopter with its corresponding mnature of flight, by Chi-square Pearson criterion is estimate mcharacter of helicopter flight, and by criterion of minimum of general dispersion of real filtration errors is estimate ĵversion of flight dynamics of helicopter for estimated value mnature of flight.EFFECT: formation of mismatch parameters in the RECS with an air-to-air missile, which enable self-guidance of the missile to the helicopter with different flight characteristics (stationary flight, flight with acceleration, flight with braking and flight in hovering mode).1 cl, 1 dwg

Method of forming error parameters in radio-electronic control system of air-to-air missile at its self-homing to helicopter with various flight type thereof

Gorbunov Sergej Aleksandrovich

Papers

Method of forming mismatch parameters in a radio-electronic system for controlling an air-to-air missile with its self-homing on an aircraft of a pair of them according to its functional purpose on the principle of "master-slave"

Method of tracking a helicopter in a pulse-doppler radar station

Method of forming error parameters in radio-electronic control system of air-to-air missile at its self-homing to helicopter with various flight type thereof