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" Russian patent published in 2019 - IPC F41G7/22 

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 horizontal and vertical planes, measurement by means of accelerometer of own acceleration of missile in horizontal J_h and vertical J_v planes, 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 estimates and trajectories 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 τ₁ and τ₂, natural frequency f₀₁ and f₀₂ autocorrelation function, root-mean-square deviation σ₁ and σ₂ fluctuations of Doppler frequency, analysis of parameters of autocorrelation functions, when conditions are met τ₁>τ₂, f₀₁<f₀₂, σ₁<σ₂ (1), decision is made that estimation of is caused by speed of approach of missile with master by aircraft of pair, and estimate is caused by speed of approach of missile to driven plane of pair, in this case at prelaunch target designation (TD) on missile guidance on master plane of mismatch parameters in the RECS in horizontal Δ_h^mr and vertical Δ_v^mr planes will be formed in accordance with expressions

where λ – operating wavelength of SGR missile; N is the navigation constant, at the pre-launch TD on the missile guidance to the driven aircraft the parameters of the mismatch are formed in accordance with the expressions

when the conditions τ₁<τ₂, f₀₁>f₀₂, σ₁>σ₂ (6), decision is made that estimate is caused by speed of approach of missile to driven plane of pair, and estimate is 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 expressions

and at prelaunch TD guidance of missile on driven aircraft from pair parameters of mismatch are formed in accordance with expressions

EFFECT: 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