RU2707200C2 - Method and device for generating adaptive radio interference - Google Patents

Abstract

FIELD: physics.

SUBSTANCE: invention relates to radioelectronic suppression of high-precision weapons control systems and can be used in development of radio countermeasures systems intended for protection of air and ground objects from hitting by self-guided missiles. Method for generating adaptive radio interference, based on detecting an attacking guided missile, determining the fact of guidance of the missile to the protected object and emission of radio interference in the direction towards the missile consists in the fact that they interfere with the missile, the phase coordinates of the missile are measured, using the measured phase coordinates of the missile, the transient characteristic of the missile guidance loop is calculated by the instantaneous miss and its parameters at the extremum point, using parameters of the point of extremum of the transient characteristic of the missile guidance system by the instant miss, determining parameters required for simulating the missile guidance circuit, by mathematical simulation in compressed time scale using mathematical model of missile guidance circuit, parameters of which are refined, calculating relationship of instantaneous miss of missile for each of available types of interferences and selecting type of interference, which provides maximum instant miss of missile, emit interference of selected type in direction towards attacking rocket. In use, the method can reduce the probability of hitting the protected objects to level of 0.1 or less.

EFFECT: technical result is high efficiency of suppression of guidance systems of guided missiles due to adaptive selection of type and parameters of interference, which takes into account parameters of guidance loop of precisely that guided missile, which attacks protected object at current moment in real time scale.

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Description

The invention relates to electronic suppression of high-precision weapon control systems and can be used in the development of radio suppression systems designed to protect air and ground targets from hitting missiles.

Known methods for creating adaptive radio interference, taking into account the response of the suppressed radar to the effects of radio interference (see, for example, Yu.M. Perunov, K.I. Fomichev, L.M. Yudin. Radio-electronic suppression of information channels of weapon control systems. M .: " Radio engineering ”, 2003. - p. 231). The essence of these methods lies in the fact that observing the effect of the influence of radio interference on the suppressed radar, the radio suppression complex selects the type of interference and its parameters based on the maximum interference efficiency achievable under current conditions.

The closest in technical essence is the method of creating adaptive interference for suppressing guided missile homing systems, based on monitoring the effectiveness of interference on trajectory grounds (see, for example, Modern electronic warfare. Methodological issues / Edited by V. G. Radzievsky. - M. : “Radio Engineering”, 2006. - p. 256). The essence of the method is to assess the effect of the impact on the homing system of a guided missile interference in the form of a false target, offset from the true target by a fixed distance. Efficiency control in this case consists in determining the aiming point of a guided missile based on the assessment of its current phase coordinates.

The disadvantages of the method are:

formation of the type and parameters of interference is carried out using pre-selected averaged parameters of the guidance loop of the attacking missile. In real conditions, in each case, the real parameters of the guidance loop of the attacking missile do not coincide with its pre-selected averaged parameters;

the choice of types and parameters of adaptive interference is carried out by the method of sequentially sorting interference effects in real time and evaluating the results of the interference, which leads to significant time costs and is not always possible in real time.

the choice of types and parameters of adaptive interference does not ensure the achievement of the maximum (potential) effectiveness of protection.

A device is known for the mutual protection of two objects from hitting a radiation-homing missile (see, for example, Yu.M. Perunov, K.I. Fomichev, L.M. Yudin. Radio-electronic suppression of information channels of weapon control systems. M., Radio engineering, 2003 d, p. 231), containing a series-connected detector of a homing missile and interference transmitters installed on protected objects or in close proximity to them.

The main disadvantage of this jamming device for suppressing guided missile guidance systems is the low jamming efficiency due to the fact that the type and parameters of the jammers are set in advance when designing the jamming means based on the assumed averaged parameters of the guiding missile guidance loop. In the general case, the types and parameters of interference specified in this way can significantly differ from those required. The values of the required types and parameters of interference, which provide the greatest suppression efficiency, depend on the parameters of the missile guidance contour in the specific current guidance conditions. The parameters of the missile guidance loop during the missile guidance on the target depend on a number of factors: the type of missile, the firing conditions, and also vary due to the unsteadiness of the guidance loop itself, due to the nature of the change in range between the missile and the target.

The technical result to which the present invention is directed is to increase the efficiency of suppressing guided missile guidance systems by adaptively choosing the type and parameters of interference, which takes into account the parameters of the guidance loop of the attacking rocket in the current guidance conditions in real time.

The technical result is achieved by the fact that in the known method of creating radio interference, based on the detection of an attacking guided missile, determining the fact of pointing the missile at the protected object and radiation of the radio noise in the direction of the missile,

interfere with a rocket,

determine the change in the phase coordinates of the rocket caused by the influence of interference,

determine by changing the phase coordinates of the rocket the parameters of the mathematical model of the missile guidance loop,

using this mathematical model of the missile guidance loop select the most effective interference

and create such a hindrance.

The technical result is achieved by the fact that in the known jamming device for suppressing guided missile guidance systems, comprising a series-connected device for detecting and measuring the phase coordinates of an attacking guided missile, as well as an interference transmitter installed on the protected object or in the immediate vicinity of it, are additionally introduced sequentially connected:

a device for calculating the transition characteristics of the guidance loop of an attacking guided missile in an instant miss,

a device for calculating the parameters of the mathematical model of the missile guidance loop,

a device for calculating the instant miss of an attacking missile using a mathematical model of the missile guidance contour in a compressed time scale for the generated types of interference,

a device for selecting the type and parameters of interference providing the maximum instant miss of the attacking rocket at the protected object,

wherein the output of the device for detecting and measuring the phase coordinates of the attacking missile is connected to the input of the device for calculating the transition characteristics of the missile guidance contour by instantaneous miss and its parameters,

the input of the interference transmitter is connected to the output of the device for selecting the type and parameters of the interference, providing the maximum instantaneous miss of the attacking rocket at the protected object.

The essence of the invention lies in the fact that for the adaptive choice of the type and parameters of the most effective interference, a mathematical model of the guidance loop of the attacking missile is used, the parameters of which correspond to the parameters of the guidance loop of the particular missile that attacks the protected object. These parameters are determined based on the measurement of the phase coordinates of the rocket, changing as a result of the effect of interference on the missile guidance loop.

The application of the method begins from the moment the attack rocket goes into homing mode. A special meter located on the protected object detects an attacking missile and measures its phase coordinates - the Doppler frequency and the range “rocket-protected object”. After the beginning of the measurement of the phase coordinates of the attacking rocket, an interference is effected on it. Further, by the nature of the change under the influence of interference of the measured phase coordinates of the rocket, the measured transitional characteristic of the guidance loop of the attacking rocket is calculated by instantaneous miss. The parameters of the extremum point of the measured transition characteristic of the missile guidance loop are determined — the amplitude maximum and the time it takes to reach it. The parameters of the mathematical model of the guidance curve of the attacking rocket are found using analytical expressions that approximate the measured transition characteristic by instantaneous miss and the parameters of its extremum point. Using a mathematical model of the guidance curve of an attacking rocket by modeling in an accelerated time scale for each of the possible types of interference generated, an instant miss of the attacking rocket over the protected object by the end of the guidance of the rocket is calculated. Choose the type and parameters of interference that provide the maximum instant miss of the attacking rocket at the protected object. Further emit such interference.

The implementation of the invention. The proposed method for creating adaptive interference can be implemented by performing the following sequence of actions.

1. The functioning of the method begins from the moment the transition of the attacking missile into homing mode. A sign of the start of homing missiles is a change in the type of backlight signal of the protected object. This fact is recorded by means of direct radio intelligence (such as an irradiation warning station) located at the protected object (see, for example, the On-board complex for navigation, aiming and weapon control of the Su-27 aircraft. Edited by MS Yarlykov. - M .: "The publication of the VVIA named after Prof. NE Zhukovsky", 1987. - p. 486).

2. A special meter (such as an airborne radar station or a radar sighting system) located on the protected object detects an attacking homing missile and measures its phase coordinates - Doppler frequency and the “rocket-protected object” range (see, for example, the airborne navigation and targeting system and weapon control of the Su-27 aircraft. Edited by MS Yarlykov. - M .: “VVIA Publishing House named after Prof. NE Zhukovsky”, 1987. - p. 156)

To obtain a transitional characteristic of a missile guidance loop by instantaneous miss, they act on the guidance loop of an attacking missile by a stepwise action with a known amplitude in accordance with (see, for example, A.A. Voronov. Theory of automatic control. Part 1. Theory of linear systems of automatic control. Textbook for universities. M., Higher School, 1977, S. 49). Such an effect can be reproduced, for example, by switching on the interference, which ensures the redirection of the attacking missile at a displaced radiation source (see, for example, the On-board complex of aircraft navigation, aiming and weapon control of the Su-27 aircraft. Edited by M. Yarlykov. - M. : “VVIA Publishing House named after Prof. NE Zhukovsky”, 1987. - p. 486).

The transient response of the missile guidance loop in instantaneous miss is calculated using the measured phase coordinates: Doppler frequency F _d (t) and the range “rocket - protected object” D _P-ЗО (t). An instant miss miss is understood to mean the projection of the missile-target line onto a plane perpendicular to the approach vector of the missile and the target passing through the target (see, for example, Neupokoev F.K. Shooting anti-aircraft missiles. - M.: Voenizdat, 1980. - p. 81).

At constant speeds and angles of approach of the attacking missile and the protected object, the time dependence of the instantaneous miss is calculated by the formula (see, for example, Kozlov S.V., Karpukhin V.I., Lazarenkov S.M. Conflict models of aircraft electronic warfare systems and air defense Monograph. - Voronezh: VUNC Air Force VVA. 2013. - p. 338):

where D _P-ЗО (t) is the dependence of the range "rocket - protected object" on time;

F _D (t) is the time dependence of the Doppler frequency of the signal reflected from the attacking rocket;

F _max ^{_ the} maximum value of the Doppler frequency of the signal reflected from the attacking rocket, determined when the rocket and the protected object meet each other.

The procedure for determining the parameters of the mathematical model of the rocket guidance loop of the smallest possible order using the transition characteristics of the rocket guidance loop for instantaneous miss is given in (see, for example, Kozlov S.V., Karpukhin V.I., Lazarenkov S.M.Conflict models of aircraft electronic systems combat and air defense. Monograph. - Voronezh: VUNC Air Force "VVA". 2013. - S. 341) and consists in the following:

determine the extremum point parameters of the measured transition characteristic of the missile guidance contour by an instantaneous miss (2) h _MAX and t _MAX — amplitude maximum and time to reach it;

The mathematical model of the missile guidance loop can be based on a structural diagram of the guided missile guidance loop with instantaneous miss (see, for example, V.V. Bykov, Yu.S. Sukhorukov. Radar homing accuracy under conditions of wandering of the radiation center and target maneuver / Modern electronic warfare. Methodological issues. Edited by Honored Scientist of the Russian Federation. VG Radzievsky. M., Radio Engineering, 2006), shown in Fig. one.

In FIG. 1 is indicated:

h _M (t T _H ) - instant miss of UR;

Y _C (t), Y _P (t) - the coordinates of the target and missiles;

K _H - navigation constant of the guidance loop of the SD;

T _V is a constant filter time commands;

T _N - the considered time interval of flight of the UR in homing mode;

t is the current time.

The differential equation describing the instantaneous miss for the mathematical model shown in FIG. 1, has the form:

Based on the solution of differential equation (3) using the method of quasi-fixed coefficients (see, for example, Dobrolensky Yu.P., Ivanova A.I., Pospelov G.S. Automation of guided missiles. Ed. By Doctor of Technical Sciences, Professor G. . S. Pospelova, M., Oborongiz, 1963) analytic expressions are obtained for an inhomogeneous differential equation that approximate the measured transient response over an instantaneous miss. These expressions allow you to determine the desired parameters of the mathematical model of the guidance loop of the rocket Kn and TF:

with the aperiodic nature of the process

with the oscillatory nature of the process

By the aperiodic nature of the process we mean the type of the transition characteristic by instantaneous miss with one maximum, and by the oscillatory nature of the process we mean the form of the transition characteristic by instantaneous miss with several periodic maxima;

constitute a system of equations that analytically describe the functioning of the mathematical model by equating expressions (4) and (5) for the instantaneous slip transition characteristic at time t _MAX to the value of its measured maximum h _M (t _MAX , T _H ) = h _MAX , and the derivative expressions (4) and (5) of the transient response — equating to zero, at time t _MAX, the maximum transient response h ' _M (t _MAX , T _H ) = 0;

determine the intermediate parameters T1, T2 and T _K , ξ _K , functions h _МА (t, Т _H ), h _MК (t, T _Н ) by solving numerically the digital systems made in paragraph 3) of the systems of equations;

calculate the parameters of the mathematical model of the missile guidance loop, which are associated with the intermediate parameters T1, T2 and T _K , ξ _K , by the following relationships:

with the aperiodic nature of the process

with the oscillatory nature of the process

Using the mathematical model of the guidance curve of the attacking rocket using mathematical modeling in an accelerated time scale for each of the possible types of interference generated, the dependences of the instant miss of the attacking rocket on the protected object from the guidance time are calculated.

The time scale for digital modeling using a mathematical model of the missile guidance loop is equal to (see, for example, Bykov V.V. Digital modeling in statistical radio engineering. - M.: "Soviet Radio", 1971 - p. 248)

where Δt _M is the time required to complete on the computer all the calculations at each modeling step;

Δt is the sampling interval of the simulated process;

N _Δ is the number of elementary operations spent in the calculation at one step;

F _M - machine speed equal to the number of elementary operations per second;

ƒ _s - sampling rate of the simulated process.

The minimum value of N _Δ is equal to unity, the doubled sampling rate of the process, in accordance with the Kotelnikov theorem, is selected on the order of the spectral width of the simulated process - this amounts to tens of hertz, and the speed of modern universal digital computers is hundreds to thousands of megahertz.

Therefore, the time scale in digital modeling can reach several hundred times, which provides a significant reduction in the time spent calculating the instant miss of the attacking rocket at the protected object for each of the possible types of interference.

The type and parameters of the interference are selected at which the maximum miss of the attacking missile relative to the protected object is achieved, thereby ensuring the maximum (potential) effectiveness of the protection of the object.

The selected interference is emitted towards the attacking rocket.

The implementation of the proposed procedure is possible using a specialized computer, implemented on the basis of a computer located on the protected object.

Studies have shown that the total time for choosing adaptive interference to suppress the guidance loop of an attacking missile does not exceed 20% of the total homing time of a rocket under typical guidance conditions, and is sufficient for the effective use of interference.

In FIG. 2 shows a block diagram of a device using which the proposed method for creating adaptive interference to suppress guided weapon guidance systems can be implemented.

On the structural diagram of the device, the numbers indicate:

1 - attack guided missile;

2 - interference transmitter installed on the protected object or in the immediate vicinity of it;

3 - a device for detecting and measuring the phase coordinates of an attacking rocket;

4 - a device for calculating the transition characteristics of the missile guidance contour for an instant miss and its parameters;

5 - a device for calculating the parameters of a mathematical model of a missile guidance loop;

6 - a device for selecting the type and parameters of interference, providing the maximum instant miss of the attacking missile at the protected object;

7 is a device for calculating the instant miss of an attacking missile using a mathematical model of the missile guidance contour in a compressed time scale for the generated types of interference.

The device differs from the selected prototype in that it additionally includes:

a device for calculating the transition characteristics of the missile guidance contour for instantaneous miss and its parameters;

device for calculating the parameters of the mathematical model of the missile guidance loop;

a device for calculating the instant miss of an attacking missile using a mathematical model of the missile guidance contour in a compressed time scale for the generated types of interference;

a device for selecting the type and parameters of interference providing the maximum instant miss of the attacking missile at the protected object.

To implement the invention can be used typical electronic components and devices.

As a special meter 3, located on the protected object, which detects an attacking homing missile and measures its phase coordinates - the Doppler frequency and the range “rocket-protected object”, an airborne radar station or a radar sighting system can be used (see, for example, the Airborne Navigation Complex , aiming and weapon control of a Su-27 aircraft. Edited by MS Yarlykov. - M .: “VVIA Publishing House named after Prof. NE Zhukovsky”, 1987. - p. 156)

Devices that sequentially perform operations of calculating the transition characteristic of the missile guidance loop for instant miss and its parameters 4, calculating the parameters of the mathematical model of the missile guidance loop 5, calculating the instant miss of the attacking missile using a mathematical model of the missile guidance loop in a compressed time scale for the generated types of interference 7, the choice of the type and parameters of interference, providing the maximum instantaneous miss of the attacking missile at the protected object 6, can be performed as a single a specialized calculator that implements sequential calculations performed 4-7 and provides maximum instant miss of the attacking guided missile (see, for example, V.P. Dyakonov. Reference on algorithms and programs in BASIC for personal computers. M. Nauka, 1987 , p. 96, 100).

To emit interference in the direction of the attacking missile, an active interference station attached to the protected object can be used as an interference transmitter 2 (see, for example, the On-board complex for navigation, aiming and weapon control of an Su-27 aircraft. Edited by M.S.Yarlykov. - M .: "VVIA Publishing House named after Prof. NE Zhukovsky", 1987. - p. 491).

To implement the invention can be used typical electronic components and devices. Therefore, the proposed technical solution is practicable.

The proposed technical solution is new, because from publicly available information there is no known way to protect objects from being hit by a homing missile, based on the detection of an attacking guided missile, determining whether the missile was pointing at the protected object and radiating radio interference in the direction of the missile, interfering with the missile, determining the change in phase coordinates missiles caused by interference, determining the parameters of the mathematical model of the cancer guidance loop by changing the phase coordinates of the rocket you selection using this mathematical model missile guidance loop interference at which the maximum instantaneous slip attacking missile to the protected object and thereby provides maximum (potentially possible) protection efficiency of the object, and a radiation noise.

From publicly available information, the jamming device for suppressing guided missile guidance systems is also unknown, which contains a device for detecting and measuring the phase coordinates of an attacking guided missile, as well as an interference transmitter installed on or in the immediate vicinity of the protected object, and a device for calculating the transient response of the loop guidance of an attacking guided missile in an instant miss; device for calculating the parameters of a mathematical model of a guidance contour missiles, a device for calculating the instant miss of an attacking missile using a mathematical model of the missile guidance contour in a compressed time scale for the generated types of interference, as well as a device for selecting the type and parameters of interference that provide the maximum instant miss of the attacking missile at the protected object, while the output of the detection and measurement device the phase coordinates of the attacking missile is connected to the input of the device for calculating the transition characteristics of the missile guidance contour for an instant miss and its parameters, in the course of the interference transmitter is connected to the output of the device for selecting the type and parameters of the interference, providing the maximum instant miss of the attacking rocket at the protected object.

The proposed technical solution has an inventive step, since the published scientific data and the known technical solutions do not explicitly imply the declared sequence of actions for determining its transitional characteristics using the measured phase coordinates of a homing missile and the parameters of the mathematical model of the missile guidance contour for instant miss, calculation of missile instant miss in a compressed time scale using a mathematical model of a missile guidance contour for Each of the available types of interference, the choice of the type and parameters of interference that provide the maximum instantaneous miss of the attacking missile at the protected object, and the emission of the most effective interference.

Claims (7)

The method of creating adaptive radio interference, based on the detection of an attacking guided missile, determining the fact of a missile pointing at a protected object and radiation of radio interference in the direction of a missile, characterized in that interfere with a rocket, measure the phase coordinates of the rocket, using the measured phase coordinates of the rocket, the transition characteristic of the missile guidance contour by instantaneous miss and its parameters at the extremum point are calculated, using the parameters of the extremum point of the transition characteristic of the missile guidance loop by instantaneous miss, determine the parameters necessary for modeling the missile guidance loop, using a mathematical simulation method in a compressed time scale using a mathematical model of the missile guidance contour, the parameters of which are refined, calculate the dependences of the missile instant miss for each of the existing types of interference, and choose the type of interference that provides the maximum instant miss miss, emit interference of the selected type in the direction of the attacking missile.

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