FIELD: physics.SUBSTANCE: invention relates to the field of secondary processing of radar signals and can be used for recognition in an impulse-Doppler radar station of the aircraft type with a turbojet engine (TJE) under action of imitating (distance and speed) interference. In the method, a signal reflected from an aircraft with a jet turbine engine is subjected to narrow-band Doppler filtration and converted to an amplitude-frequency spectrum. Further, in the first Kalman filter, estimating the Doppler frequencycaused by reflections of signal from aircraft airframe, in second Kalman filter is estimated Doppler frequencycaused by signal reflection from advancing blades, and in fourth Kalman filter from aircraft first stage low-pressure compressor first stage impeller turbo blades. Differential derivative difference estimatoris compared between estimated values of Doppler frequencies with threshold value e, close to zero, and decision is made on presence or absence of action of speed-escaping interference. In the third Kalman filter, a difference module is compared between the estimate of the range derivative to the aircraftand the estimate of the speed of approach of the radar station with the accompanying aircraftwith the threshold e1, the difference module between the range estimateand the calculated range D*(k) - with the threshold e2. Depending on the results of comparison with threshold values, a decision is made on the presence or absence of the effect of intervening speed and range noise with/without a functionally related law. Entire range of possible values of estimates of differencesis divided into Q non-overlapping subranges depending on the value of rotation speed of the rotor of the power plant, calculating probability Pqof falling of valuein each of formed q-x subbands. Maximum value of probability is compared with threshold value, and at Pqmax ≥ Pthrdecision is made on recognition of q-type aircraft with turbojet engine with probability Pqmaxnot lower than specified.EFFECT: technical result is recognition in pulse-Doppler radar station with probability not lower than the specified type of aircraft with turbojet engine at effect of interruptions in range and speed of interference.1 cl, 4 dwg

Method of aircraft type identification with turbojet engine in pulse-doppler radar station under action of simulating noise

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: 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: radar ranging.SUBSTANCE: invention relates to the field of radar ranging and can be used for recognition in a Pulse-Doppler radar of aircraft type with turbojet engine (TE). Method of aircraft type identification with TE in pulse-Doppler radar station consists in the fact that radar signal reflected from aircraft with TE, from the output of the receiver of the radar station at an intermediate frequency is subjected to narrow-band Doppler filtration based on the fast Fourier transformation procedure and is converted to an amplitude-frequency spectrum (AFS), which spectral components are caused by reflections of signal from airframe of aircraft with TE and rotary blades of impeller of low pressure compressor (LPC) of its power plant, by threshold processing of AFS signal only those Doppler frequencies are formed, which have exceeded the set threshold, during time T of each space survey, two distance values Dand Dto aircraft with TE, from which frequency position of Doppler frequency, caused by speed of approach of radar station carrier with airframe of aircraft with TE, in AFS signal closest to pre-calculated frequency position of Doppler frequency. Doppler frequency valuewith corresponding amplitudespectral component, which exceeds the established threshold, which finally determines Doppler signal frequency Fin its AFS, determined by the speed of approach of the carrier of the radar station to the airframe of the aircraft with the TE, the position of the Doppler frequency(j=1, …, (i-1), (i+1), …, N), on which there is a spectral component which has exceeded the threshold and having a maximum amplitude A(j=1, …, (i-1), (i+1), …, N), which corresponds to Doppler frequency value F, due to the speed of approach of the radar station carrier to the LPC first stage rotary blades of aircraft powerplant with the TE, the Doppler frequency difference is calculated ΔF=(F-F), a range of differences is divided a priori ΔFon Q non-overlapping q subbandscorresponding to the q-th type of the target, when the difference of Doppler frequencies falls ΔFdecision on q-th type of aircraft with TE is made in q-th subrange.EFFECT: high reliability of aircraft type identification with TE.1 cl, 4 dwg

Method of aircraft with turbojet engine type identification in pulse-doppler radar station

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: secondary processing of radar signals.SUBSTANCE: method consists in that a signal reflected from an aircraft with a TJE from an output of a pulse-Doppler RLS receiver at an intermediate frequency is subjected to narrow-band Doppler filtration based on a Fast Fourier Transform (FFT) and is converted into amplitude-frequency spectrum of reflection of signal from aircraft airframe with turbojet engine and rotating blades of impeller of low-pressure compressor (LPC) of its power plant. Doppler frequency count is determined, which corresponds to maximum amplitude of spectral component of reflection signal spectrum from airframe. In the first Kalman filter, the Doppler frequency(k) of the signal reflections from the airframe is estimated, in the second Kalman filter—evaluation of Doppler frequency(k) of signal reflections from impeller blades of first stage LPC of aircraft power plant, in third Kalman filter—assessment of range R(k) to aircraft, calculating a difference module of estimates(k) and(k) based on the derived range estimate, its comparison with a threshold close to zero. If the threshold is not exceeded, the conclusion is made that there is no effect of rate-escalating interference, otherwise it is a decision on the effect of speed-escaping interference. Range of estimates of the differences Δ(k) and Δ(k) is broken down into Q nonoverlapping subranges. In solving the lack of impact of escapist speed calculated interference probability Pfalling value of Δ(k) in each q-th sub-band, and at the decision of the impact of noise escapist speed calculated probability Pfalling value of Δ(k) in each q-th sub-band. Maximum probability value is compared with the threshold value of the aircraft type recognition probability. If the threshold is exceeded, the decision to recognize the q-type aircraft with the TJE is performed with probability P.EFFECT: achieved technical result is possibility of recognition in pulse-Doppler radar station with probability not below specified, type of aircraft with TJE under action of speed-escaping interference.1 cl, 5 dwg

Method of aircraft with turbojet engine type identification in pulse-doppler radar station under action of speed-escaping interference

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

Kovalenko Aleksandr Grigorevich

Papers

Method of aircraft with turbojet engine type identification in pulse-doppler radar station

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 aircraft with turbojet engine type identification in pulse-doppler radar station under action of speed-escaping interference

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