RU2292523C2 - Mode of functioning of data-processing systems of rocket and arrangement for its execution - Google Patents

Abstract

FIELD: the invention refers to military technique and designed for guidance of a rocket against an air target and information ensuring functioning of combat outfitting of the rocket.

SUBSTANCE: the essence of the invention is in that that on the basis of initial information about an angular position and distance to the target in immediate proximity from the target the speed of approach of the rocket, the missing of the rocket, geometric sizes of the target is defined. The foreshortening of the target is also determined and a command for blowing up of the warhead of the rocket with taking into consideration the information and the initial speed of recession of fragments of the warhead of the rocket is formed, by means of an arrangement having in its composition the first key and a computer of forming the command for blowing the warhead of the rocket, whose first and the second inputs are connected correspondingly with the first and the second outputs of the information processing module, the third input - with the output of the receiver of the reflected signal. The fourth input of the computer is connected with the second output of the system of autonomous sensors, the first output is connected with the second input of the first key, whose first input is connected with the second output of the channel of antenna control. The output of the first key is connected with the first input of the power amplifier and the driving gear of the antenna, whose second input is connected with the second output of the computer of forming the command for blowing up the warhead of the rocket, whose third output is the output of the command for blowing up the warhead of the rocket.

EFFECT: increases effectiveness of combat application of the rocket at the expense of using additional information about an air target and the parameters of its moving.

16 cl, 9 dwg

Description

The invention relates to the field of aviation guided missiles and can be used to solve the problem of pointing the missile at an air target and for information support of the functioning of the AUR combat equipment.

A known method of functioning of an information-computer system (IVS) of a rocket is to measure the parameters of the target’s motion and the rocket’s own motion, to generate the necessary parameters of relative and absolute motion that are not directly measurable, using a priori information, and choosing the best method for guiding the rocket at the target any criterion for the given conditions of use, the analysis of the interference situation and the inclusion, depending on the situation, of the means of noise protection, non-radio to technical gauges, retargeting missiles on the jammer, the formation and training of the control signal for the fuze (Merkulov, V.N.Lepin Aircraft Radio Control System -.. Moscow .: Radio and Communications, 1997 -. S.201).

A device is known, which includes a serially connected synchronization signal receiver, a reflected signal receiver, as well as a system of autonomous sensors and an information processing module, a computer and a power amplifier, the output of the synchronization receiver being connected to the first input of the information processing module, the output of the reflected signal receiver being the second input of the information processing module, the first and second output of the sensor system, respectively, with the third and fourth inputs of the information processing module, the fifth input it is connected to a power amplifier and an antenna drive, which is mechanically connected to the antenna, the first, second, third and fourth outputs of which are connected respectively to the control signal and feedback signal bus to the fighter’s equipment, to the first and second input of the mismatch parameters calculator, to the amplifier input power and drive the antenna, the output of which has a mechanical connection with the antenna (Merkulov, V.N. Lepin. Aircraft radio control systems. - Moscow .: Radio and communications. 1997 - S.201).

The disadvantage of the data of the method and device is the poor information support of the functioning of the AUR combat equipment due to the lack of the possibility of obtaining additional information about the air target and its motion parameters on board the rocket.

An object of the invention is to increase the effectiveness of the combat use of missile defense by using additional information about the air target and its movement parameters in the interests of combat equipment of the anti-missile defense class.

The solution to the technical problem is achieved by the fact that in the method of functioning of the information and computing system of the rocket, which consists in measuring the parameters of the target’s motion and the rocket’s own motion, forming the necessary parameters of relative and absolute motion that cannot be measured directly, using a priori information, choosing the method of guiding the rocket at the goal, the best by any criterion for the given conditions of use, analysis of the interference environment and inclusion, depending on the situation The jammers of anti-jamming means and non-radio technical meters, re-targeting the rocket to the jammer, generating a training and control signal for the radio fuse, are additionally determined based on the initial information about the angular position and the distance to the target, in the immediate vicinity of the target, the speed of approach of the rocket, the geometric dimensions of the target, miss missiles and form a team to undermine the warhead of the rocket based on this information, taking into account the initial speed of the flight of fragments of the warhead of the rocket.

The speed of approach of the rocket in the immediate vicinity of the target is determined at the moment the target passes the second and third fixed distances in the form of the expression:

where Z ₂ , Z ₃ are the second and third fixed distances to the target, τ is the time interval proportional to the speed of the target when passing through these fixed distances.

The linear size of the extended target is determined at the moment it passes the second fixed distance by scanning it with a radiation pattern and fixing the angular positions and the distance to the starting and ending points on the extended target, respectively, at the time the reflected signal appears and disappears from the target in the form of the expression:

where D ₁ , D ₂ - the angular position of the start and, respectively, the end point on the target body; Δφ = φ _n -φ _to - the angular size of the target.

The miss miss value is determined in the form of the expression:

where A, B, C are constant coefficients, r ₁ , r ₂ , r ₃ are the current distances recorded during the passage of the target three given distances.

The perspective of the goal is determined in the form of an expression:

where V _r , V _c are the rocket and target velocity modules, β is the angle between the components of the target vector, Δφ is the angular size between two fixed points relative to the rocket, r _n , r _{n + 1} are the current values of the range to the target.

Form a team to undermine the warhead of the rocket in the form of the following algorithms:

- if the objective angle q> q _p , then in the form:

where V ₀ - the initial velocity of the expansion of fragments;

- if q <q _p and V _sb. <V _p , then in the form:

- if q <q _p and V _sb. > V _p , then in the form:

A device for functioning of an information-computing system comprises a serially connected antenna and a receiver of a synchronization signal, an antenna and a receiver of a reflected signal, an information processing module and a mismatch parameters calculator, as well as a system of autonomous sensors, a power amplifier and an antenna drive, the information processing module consists of a search device, detection, selection and analysis of signals, channel for estimating range and speed of approach, antenna control channel, and its output is mechanically connected with the antenna of the reflected signal, the output of the reflected signal receiver is connected to the first input of the information processing module, the second, third, fourth, fifth, sixth, seventh inputs of which are respectively connected to the first output of the synchronization signal receiver, the first and second outputs of the autonomous sensor system, the output of the training and target designation commands from the fighter equipment, which are simultaneously connected to the third input of the mismatch parameters calculator, with the output of the autonomous system calculator, the first output the power amplifier and the antenna drive, the second output of which is mechanically connected to the antenna of the detached signal, while the first, second, third outputs of the information processing module are connected respectively to the input of the control and feedback signals of the fighter equipment, the first and second inputs of the mismatch parameter calculator, in addition , the second output of the synchronization receiver is connected to the second input of the reflected signal receiver, an additional key and a computer for generating a command to undermine the warhead you, the first, second inputs of which are connected respectively to the first and second outputs of the information processing module, the third input is with the output of the reflected signal receiver, and the fourth input is with the second output of the autonomous sensor system, the first output is connected to the second input of the first key, the first input of which connected to the second output of the antenna control channel, and the output of the first key is connected to the first input of the power amplifier and the antenna drive, the second input of which is connected to the second output of the command generation calculator the warhead of the missile, the third exit of which is the exit of the team to undermine the warhead of the rocket.

In addition, the team formation calculator for undermining the warhead of the rocket consists of a block for fixing the current parameters of the target’s movement, a block for determining missile missiles, a block for determining the geometrical dimensions of the target, a block for determining the angle of the target, and a block for forming the team for undermining the warhead of the rocket, the first, second, the third and fourth inputs of the team formation calculator for detonating the warhead of the rocket are respectively the first and second inputs of the unit for fixing the current parameters of the target’s movement, the unit for determining ge the metric dimensions of the target, the block for determining the angle of the target, the fifth input of the block for determining the geometric dimensions of the target and the fourth input of the block for determining the angle of the target, the first, second, third, fourth, fifth and sixth outputs of the block for fixing the current parameters of the target are connected respectively to the first, second and third inputs missile miss detection unit, the second input of the command formation unit to detonate the missile warhead, the third input of the target geometrical size determination unit, and the third input of the command formation unit to undermine the warhead of the rocket and simultaneously the fourth input of the block for determining the geometric dimensions of the target, the output of the block for determining miss missiles is connected to the first input of the unit for forming the team for the detonation of the warhead of the rocket, the first, second and third outputs of the block for determining the geometric dimensions of the target are connected respectively to the second input of the amplifier power and drive the antenna, the fourth and fifth inputs of the unit forming the team to detonate the warhead of the rocket, the fourth input of which is connected to the third input of the unit is determined of the view of the target, the output of which is connected to the sixth input of the command formation unit for undermining the warhead of the rocket, the fifth output of the block for fixing the current parameters of the target’s movement, the first output of the unit for determining the geometric dimensions of the target and the output of the command formation block to undermine the warhead of the rocket are respectively the first, second and the third outputs of the team formation calculator to undermine the warhead of the rocket.

In addition, the unit for fixing the current target motion parameters consists of a first functional converter, a first multiplier, first, second and third comparators, first, second and third storage devices, as well as a constant signal generator, the first and second inputs of the unit for fixing current motion parameters the goals are respectively the input of the first functional converter and the first inputs of the first, second, third storage devices, the first multiplier, the second input of which is connected nen with the output of the first functional converter, and the output is connected to the first inputs of the first, second, and third comparators, the second inputs of which are connected respectively to the first, second, third outputs of the constant signal generator, and the outputs of the first, second, and third comparators are connected to the first inputs the first, second and third storage devices, the outputs of which, as well as the output of the third comparison device and the fourth output of the first constant signal generator, are respectively the first, second, third, fourth and fifth outputs of the block fixing the current parameters of the movement of the target.

In addition, the missile miss detection unit consists of the first, second and third quadrators, the second, third multipliers, the first subtracting and second summing devices, the second functional converter, as well as the second constant signal generator, the first, second and third inputs of the miss detection unit rockets are respectively the inputs of the first, second and third quadrators, the outputs of which are connected respectively to the first inputs of the second, third and fourth multipliers, the second inputs of which are connected to the first, second and third outputs of the second constant signal generator, the outputs of the second, third and fourth multipliers are connected respectively to the first and second inputs of the first subtractor and the second input of the second summing device, the first input of which is connected to the output of the first subtractor, and the output - with the input of the second functional Converter, the output of which is the output of the missile miss detection unit.

In addition, the unit for determining the geometric dimensions of the target consists of the first element AND, the first element AND, the first pulse generator, pulse counter and series-connected first shift register, digital-to-analog converter, as well as from the third, fourth, fifth and sixth storage devices, the third and the fourth quadrators, the third adder, the second and third subtracting devices, the third and fourth functional converters, the fifth multiplier, the third constant signal generator, moreover, the first, second, third, fourth and fifth inputs of the block for determining the geometric dimensions of the target are respectively the first inputs of the third and fourth, fifth and sixth storage devices, the second input of the first element And, the second input of the counter, the first input of the first element And and the input of the first element And -NOT, the output of the first element AND is NOT connected to the second input of the first shift register and simultaneously with the second inputs of the fourth and sixth storage devices, the output of the first element And is connected to the input of the first pulse generator and simultaneously with the second inputs of the third and fifth storage devices, the output of the first pulse generator is connected to the first input of the first shift register and simultaneously with the first input of the pulse counter, n - outputs of the first shift register are connected to n - inputs of the digital-to-analog converter, the outputs of the third, fourth , the fifth and sixth storage devices are connected respectively to the inputs of the third and fourth quadrators, the first and second inputs of the fourth subtractor, except the outputs of the third and fourth storage devices are connected to the first and second inputs of the fifth multiplier, the outputs of the third and fourth quadrants are connected to the first and second inputs of the third adder, the output of which is connected to the first input of the second subtractor, the output of the third subtractor is connected to the input of the third functional a converter whose output is connected to the third input of the fifth multiplier, the fourth input of which is connected to the output of the third constant signal generator, and the output is connected nen with a second input of the second subtractor, whose output is connected to the input of the fourth function converter, outputs a digital to analog converter, a counter and a fourth function converter are respectively first, second and third determination unit outputs target geometrical sizes.

In addition, the target angle determination unit consists of an integrator, sixth, seventh and eighth multipliers, first and second dividers, fifth, sixth, seventh, eighth, ninth and tenth functional converters, fifth, sixth, seventh, eighth and ninth subtractive devices, second , the third, fourth and fifth keys, the second shift register and the second pulse generator, the first, second, third and fourth inputs of the unit determining the angle of view of the target are respectively the first inputs of the second and third, h the fourth and fifth keys, the first input of the sixth subtractor and the integrator input, the output of which is connected to the first inputs of the sixth multiplier and the second input of the sixth subtractor, the output of which is connected to the second input of the first divider, the first input of which is connected to the output of the sixth multiplier, the second input of which connected to the output of the sixth functional converter, the input of which is connected to the output of the seventh subtracting device, the output of the first divider is connected to the input of the fifth functional pre a developer, the output of which is connected to the first input of the fifth subtractor, the second input of which is connected to the output of the eighth functional converter, the output of which is also connected to the second input of the seventh subtractor, the output of the fifth subtractor is connected to the input of the seventh functional converter, the outputs of the second, third, fourth and the fifth keys are connected respectively to the first inputs of the eighth subtractor, the seventh and simultaneously the eighth multipliers, the first and second inputs the ninth subtractor, the first input of which is simultaneously connected to the first input of the seventh subtractor, the output of which is connected to the input of the sixth functional converter, the outputs of the seventh and eighth multipliers are connected respectively to the second inputs of the eighth subtractor and the second divider, the first input of which is connected to the output of the eighth of the subtracting device, and the output is with the input of the eighth functional converter, the output of the ninth subtracting device is connected to the inputs of the nine of that and tenth functional converters, the outputs of which are connected respectively to the second inputs of the seventh and eighth multipliers, the output of the second pulse generator is connected to the input of the second shift register, the first and second outputs of which are connected respectively to the second inputs of the fourth and second, fifth and third keys, the seventh output functional converter is the output of the block definition of the angle of the target.

In addition, the team formation unit for undermining the warhead of the rocket consists of the third, fourth and fifth dividers, the ninth multiplier, the ninth subtractor, the fourth and fifth summing devices, the fourth and fifth comparing devices, the second and third NAND elements, the second and third elements And, the sixth, seventh and eighth keys, the fourth setter of constant signals, and the first, second, third, fourth, fifth and sixth inputs of the unit forming the team to undermine the warhead of the rocket are respectively the first and second inputs of the fourth, third dividers, the first input of the fifth divider, the input of the fifth comparison device, in addition, the second input of the third divider is connected to the second input of the fifth divider and to the second input of the fourth comparison device, the outputs of the third, fourth and fifth dividers are connected, respectively with the first, second inputs of the ninth subtractor and the first input of the ninth multiplier, the output of which is connected to the third input of the ninth subtractor, the first, second, third , the fourth, fifth outputs of the fourth constant signal generator are connected respectively to the first inputs of the fifth and fourth comparing devices, the second inputs of the sixth, seventh and eighth keys, the outputs of the fourth and fifth comparing devices are connected to the first inputs of the second element And and the third element AND-NOT, the sixth key and the second AND-NOT element, the output of which is connected to the second input of the second AND element and the first input of the third AND element, the outputs of which are respectively connected to the first inputs with the seventh and eighth keys, the outputs of which are connected respectively to the second input of the fourth summing device and the second input of the fifth summing device, the first input of which is connected to the output of the sixth key, and the output to the second input of the ninth multiplier, the output of which is connected to the third input of the ninth subtracting device, the output of which is connected to the first input of the fourth summing device, the output of which is the output of the team formation unit to undermine the warhead of the rocket.

Comparative analysis with the prototype shows that the inventive method and device are distinguished by the presence of new actions, new circuit elements and new connections that provide the technical result of the invention, which allows us to conclude that in this technical solution the patentability criterion is "novelty", namely in the method:

- determine the speed of approach of the rocket with the goal at the time of passage of the second and third fixed distances;

- determine the geometric dimensions of the target;

- determine miss missiles relative to the target;

- determine the angle of the goal;

- form a team to undermine the warhead of the rocket based on this information, taking into account the speed of the expansion of fragments of the warhead of the rocket, and the first key and the calculator of the formation of the team to undermine the warhead of the rocket are entered into the device.

Comparison of the proposed solution with other technical solutions shows that it does not explicitly follow from the prior art, the claimed method and device have expanded functionality by controlling the moment of operation of the AUR warhead in accordance with the specific conditions of the missile’s approach to the target.

This allows us to conclude that the claimed invention meets the criterion of "significant differences".

Figure 1 shows the structural diagram of the information and computing system of the rocket, figure 2, 3 is a diagram of the rapprochement of the rocket with the goal, figure 4 is a structural diagram of the computer calculator formation to detonate the warhead of the rocket, figure 5 is a block fixing current parameters movement of the target, in Fig.6 is a block for determining the miss; in Fig.7 is a block for determining the geometric dimensions of the target, Fig.8 is a block for determining the angle of the target, Fig.9 is a block for forming a team to undermine the warhead of the rocket.

The device (figure 1) for the functioning of the information-computing system contains a series-connected antenna 1 and a synchronization signal receiver 2, an antenna 3 and a reflected signal receiver 4, an information processing module 5 and a mismatch parameter calculator 6, as well as an autonomous sensor system 7, an amplifier 8 power and antenna drive, key 12 and calculator 13 forming a team to detonate the warhead of the rocket, information processing module 5 consists of a device 9 for searching, detecting, selecting and analyzing signals, channel 10 range and speed of approach, channel 11 control the antenna, and its output is mechanically connected to the antenna 3 of the reflected signal, the output of the receiver 4 of the reflected signal is connected to the first input of the information processing module 5, the second, third, fourth, fifth, sixth, seventh inputs of which, respectively connected to the first output of the receiver 2 synchronization signals, the first and second outputs of the system 7 of autonomous sensors, with the output of the training and target designation commands from the equipment of the fighter, which are simultaneously connected to the third by the calculator 6 mismatch parameters, with the output of the autonomous system calculator, the first output of the power amplifier 8 and the antenna drive, the second output of which is mechanically connected to the antenna 3 of the reflected signal, while the first, second, third outputs of the information processing module 5 are connected respectively to the input of the control signals and feedback of the fighter equipment, the first and second inputs of the calculator 6 mismatch parameters, in addition, the second output of the synchronization receiver 2 is connected to the second input of the receiver 4 wife signal, the first, second inputs of the calculator 13 forming a command to detonate the warhead of the rocket are connected respectively to the first and second outputs of the information processing module 5, the third input to the output of the reflected signal receiver 4, and the fourth input to the second output of the autonomous sensor system 7, the first output is connected to the second input of the key 12, the first input of which is connected to the second output of the antenna control channel 11, and the output of the key 12 is connected to the first input of the power amplifier 8 and the antenna drive, the second input of which is connected with the second output of the calculator 13 of the formation of the team to undermine the warhead of the rocket, the third exit of which is the exit of the team to undermine the warhead of the rocket.

The calculator 13 of the formation of a command to detonate the warhead of a rocket consists of a block 14 for fixing the current parameters of the target’s movement, a block 15 for determining miss missiles, a block 16 for determining the geometrical dimensions of the target, a block 17 for determining the angle of the target and block 18 for forming a command for undermining the warhead of the rocket, the first , the second, third and fourth inputs of the calculator 13 forming the team to detonate the warhead of the rocket are respectively the first and second inputs of block 14 for fixing the current parameters of the target’s movement, block 15 for determining the geometric dimensions of the target, the block 16 determining the angle of the target, the fifth input of the block determining the geometric dimensions of the target and the fourth input of the block 17 determining the angle of the target, the first, second, third, fourth, fifth and sixth outputs of the block 14 for fixing the current parameters of the target are connected respectively to the first, second and the third inputs of the missile miss determination block 15, the second input of the command formation block 18 to detonate the missile warhead, the third input of the target geometric determination block 16, and the third input of the formation block 18 command to undermine the warhead of the rocket and simultaneously the fourth input of the block 16 for determining the geometric dimensions of the target, the output of the block 15 for determining miss missiles is connected to the first input of the block 18 for forming a team for undermining the warhead of the rocket, the first, second and third outputs of the block 16 for determining the geometric dimensions of the target connected respectively to the second input of the power amplifier 8 and the antenna drive, the fourth and fifth inputs of the command formation unit 18 to detonate the missile warhead, the fourth input of which is connected to the input of the block for determining the angle of the target, the output of which is connected to the sixth input of the block 18 of the formation of the command to detonate the warhead of the rocket, the fifth output of the block for fixing the current parameters of the target’s movement, the first output of the block 16 for determining the geometric dimensions of the target and the output of the block of the formation of the command 18 for the detonation of the battle parts of the rocket are respectively the first, second and third outputs of the computer 13 forming the team to undermine the warhead of the rocket.

Block 14 for fixing the current parameters of the target’s motion consists of the first 18 functional transducers, the first 19 multipliers, the first 20, the second 21 and the third 22 comparison devices, the first 23, the second 24 and the third 25 storage devices, as well as a constant signal generator 26, the first and the second inputs of the block 14 fixing the current parameters of the motion of the target are respectively the input of the first 18 functional converter and the first inputs of the first 23, second 24, third 25 storage devices, the first 19 multiplier, the second input which is connected to the output of the first 18 functional converter, and the output is connected to the first inputs of the first 20, second 21 and third 22 comparison devices, the second inputs of which are connected respectively to the first, second, third outputs of the constant signal generator 26, and the outputs of the first 20, second 21 and third 22 comparison devices are connected to the first inputs of the first 23, second 24 and third 25 storage devices, the outputs of which, as well as the output of the third 22 comparison device and the fourth output of the first 26 setpoint constant s signals are respectively first, second, third, fourth and fifth block 14 outputs the current fixation target motion parameters.

Block 15 missile missile determination consists of the first 28, second 29 and third 30 squads, second 31, third 32 multipliers, first 34 subtracting and second 35 totalizing devices, second 36 functional converter, and also from the second 37 constant signal generator, and the first, the second and third inputs of the missile miss detection block 15 are respectively the inputs of the first 28, second 29 and third 30 quadrators, the outputs of which are connected respectively to the first inputs of the second 31, third 32 and fourth 33 multipliers, second the inputs of which are connected respectively to the first, second and third outputs of the second 37 constant signal generator, the outputs of the second 31, third 32 and fourth 33 multipliers are connected respectively to the first and second inputs of the first 34 subtractor and the second input of the second 35 summing device, the first input of which is connected with the output of the first 34 subtractor, and the output with the input of the second 36 functional converter, the output of which is the output of the missile miss detection unit 15.

Block 16 determining the geometric dimensions of the target consists of the first 38 element AND, the first 39 element AND, the first 40 pulse generator, counter 41 pulses and connected in series to the first 42 shift register, digital-to-analog converter 43, as well as from the third 44, fourth 45, fifth 46 and sixth 47 memory devices, third 48 and fourth 49 quadrants, third 50 adders, second 51 and third 52 subtractors, third 53 and fourth 54 functional converters, fifth 55 multiplier, third 56 master constant signals, and the first, second, third, fourth and fifth inputs of the block 16 for determining the geometric dimensions of the target are, respectively, the first inputs of the third 44 and fourth 45, fifth 46 and sixth 47 memory devices, the second input of the first element And, the second input of the counter, the first input the first 38 AND elements and the input of the first 39 AND-NOT elements, the output of the first 39 AND elements NOT connected to the second input of the first 42 shift register and simultaneously with the second inputs of the fourth 45 and sixth 47 memory devices, the output is first o 38 element And is connected to the input of the first 40 pulse generator and simultaneously with the second inputs of the third 44 and fifth 46 memory devices, the output of the first 40 pulse generator is connected to the first input of the first 42 shift register and simultaneously with the first input of the counter 41 pulses, n - outputs of the first 42 shift registers are connected to n - inputs of the digital-to-analog converter, the outputs of the third 44, fourth 45, fifth 46 and sixth 47 memory devices are connected respectively to the inputs of the third 48 and fourth 49 quadrants, trans the first and second inputs of the fourth 52 subtractor, in addition, the outputs of the third 44 and fourth 45 memory devices are connected to the first and second inputs of the fifth 55 multiplier, the outputs of the third 48 and fourth 49 quadrants are connected to the first and second inputs of the third 50 adder, the output of which is connected with the first input of the second 51 subtractor, the output of the third 52 subtractor is connected to the input of the third 53 functional converter, the output of which is connected to the third input of the fifth 55 multiplier, the fourth input to which is connected to the output of the third 56 constant signal generator, and the output is connected to the second input of the second 51 subtractor, the output of which is connected to the input of the fourth 54 functional converter, the outputs of the digital-to-analog converter 43, counter 41 and the fourth functional converter 54 are respectively the first, second, and third the outputs of the block 16 determine the geometric dimensions of the target.

The target angle determination unit 17 consists of an integrator 57, sixth 58, seventh 59 and eighth 60 multipliers, first 61 and second 62 dividers, fifth 63, sixth 64, seventh 65, eighth 66, ninth 67 and tenth 68 functional converters, fifth 69, sixth 70, seventh 71, eighth 72 and ninth 73 subtracting devices, second 74, third 75, fourth 76 and fifth 77 keys, second 78 shift registers and second 79 pulse generators, the first, second, third and fourth inputs of the angle detection unit 17 goals are accordingly first the inputs of the second 74 and third 75, fourth 76 and fifth 77 keys, the first input of the sixth 70 subtractor and the input of the integrator 57, the output of which is connected to the first inputs of the sixth 58 multiplier and the second input of the sixth 70 subtractor, the output of which is connected to the second input of the first 61 a divider, the first input of which is connected to the output of the sixth 58 multiplier, the second input of which is connected to the output of the sixth 64 functional converter, the input of which is connected to the output of the seventh 71 subtractor, the output of the first 61 divides spruce is connected to the input of the fifth 63 functional converter, the output of which is connected to the first input of the fifth 69 subtractor, the second input of which is connected to the output of the eighth 66 functional converter, the output of which is also connected to the second input of the seventh 71 subtractor, the output of the fifth 63 subtractor the input of the seventh 65 functional converter, the outputs of the second 74, third 75, fourth 76 and fifth 77 keys are connected respectively to the first inputs of the eighth 72 subtractor VA, the seventh 59 and simultaneously the eighth 60 multipliers, the first and second inputs of the ninth 73 subtractor, the first input of which is simultaneously connected to the first input of the seventh 71 subtractor, the output of which is connected to the input of the sixth 64 functional converter, the outputs of the seventh 59 and eighth 60 multipliers are connected respectively, with the second inputs of the eighth 72 subtractor and the second 62 divider, the first input of which is connected to the output of the eighth 72 subtractor, and the output with the input of the eighth 66 function of the first converter, the output of the ninth 73 subtractor is connected to the inputs of the ninth 67 and tenth 68 of the functional converter, the outputs of which are connected respectively to the second inputs of the seventh 59 and eighth 60 multipliers, the output of the second 79 pulse generator is connected to the input of the second 78 shift register, the first and second outputs which are connected respectively to the second inputs of the fourth 76 and second 74, fifth 77 and third 75 keys, the output of the seventh 65 functional converter is the output of the determination unit akursa goal.

Block 18 of the formation of a team to undermine the warhead of a rocket consists of a third 80, fourth 81 and fifth 82 dividers, ninth 83 multipliers, ninth 84 subtractors, fourth 85 and fifth 86 summing devices, fourth 87 and fifth 88 comparison devices, second 89 and third 90 AND-NOT elements, the second 91 and the third 92 AND elements, the sixth 93, the seventh 94 and the eighth 95 keys, the fourth 96 constant signal generator, the first, second, third, fourth, fifth and sixth inputs of the command formation unit 18 to undermine the battle parts of rake you are the first and second inputs of the fourth 81, third 80 dividers, the first input of the fifth 82 divider, the input of the fifth 88 comparator, in addition, the second input of the third 81 divider is connected to the second input of the fifth 82 divider and the second input of the fourth 87 comparator the outputs of the third 80, fourth 81 and fifth 82 dividers are connected respectively to the first, second inputs of the ninth 84 subtractor and the first input of the ninth 83 multiplier, the output of which is connected to the third input of the ninth 84 subtract the first, second, third, fourth, fifth outputs of the fourth constant signal master 96 are connected respectively to the first inputs of the fifth 88 and fourth 87 comparison devices, the second inputs of the sixth 93, seventh 94 and eighth 95 keys, the outputs of the fourth 87 and fifth 88 comparison devices are connected respectively with the first inputs of the second 91 AND elements and the third 90 AND elements, the sixth 93 keys and the second 89 AND elements, the output of which is connected to the second input of the second 89 AND elements and the first input of the third 90 elements And, the outputs of which are respectively connected to the first inputs of the seventh 94 and eighth 95 keys, the outputs of which are connected respectively to the second input of the fourth 85 summing device and the second input of the fifth 86 summing device, the first input of which is connected to the output of the sixth 93 key, and the output to the second the input of the ninth 83 multiplier, the output of which is connected to the third input of the ninth 84 subtractor, the output of which is connected to the first input of the fourth 85 summing device, the output of which is the output of the block 18 ation teams at undermining warhead missiles.

The device operates as follows.

The functioning of the IV-V-in missile is carried out in the following modes: target designation, search and detection of a target when it is captured along the trajectory, formation of a mismatch parameter, and formation of a command to undermine the warhead of the rocket.

The first two modes are preparatory, and the actual homing and team formation to undermine the warhead of the rocket are carried out in the third mode. In the target designation mode (CC) from the equipment of the fighter to the information processing module 5, instructions are received for preparing the rocket for operation and command for the control (Fig. 1). According to the preparation commands, supply voltages to the IVS are supplied, the receivers of 2, 4 synchronization channels and the reflected signal are tuned to the frequency of the target illumination signal (TWS), and the performance of all missile equipment is tested. At the command of the controllers, the meters and calculators are prepared to track the target selected for destruction. In accordance with these commands, the antenna 3 of the homing head is deployed in the direction of the target or at the anticipated point at which the target will be located at the time of taking it for auto tracking. The presence of target designation commands for the range of D _tsu and approach speed V _tsu is determined by the guidance method used and the target illumination signal.

If a continuous TWS is used in the homing radar (RGS), then the command is given for the approach speed V _zu (Doppler frequency), in accordance with which radio signals will be selected only for that target, the approach speed with which corresponds to the target designation speed. If the CSG SPO uses pulse, the processing unit 5 receives the command MC by range, whereby the reflected signal receiver will be unlocked only during the arrival of the signals reflected from the target, separated from the fighter in the desired distance D _zu. In case of a quasi-continuous TWS, the commands of the control center are given both in range and speed. In addition, the command of the control center in range, approach speed, and angular velocities of the line of sight comes as initial conditions to calculators that extrapolate the relative motion of the rocket and the target in the autonomous mode of the IVS, preceding the capture of the target on the trajectory, and in the event of interference with it. The readiness of the IVS for work is controlled by a special control signal supplied to the fighter’s equipment via feedback circuits (Fig. 1).

It should be noted that, depending on the type of target illumination signal (TWS), the search and selection of the signal reflected from the intercepted target are performed differently.

After the coincidence in time of the tracking half-gates of the rangefinder and the pulse u _c reflected from the target, the search stops and the detection problem is solved. In the process of solving this problem, signals are accumulated, with the aim of increasing the probability of correct detection. In addition, the detected signal is analyzed for its belonging to the target or the jammer. The analysis is performed according to the energy criterion, since the direct signal of active interference is many times higher than the signal reflected from the target.

If in the process of analysis it is decided that the detected signal belongs to the jammer, then the noise immunity means is turned on, or they continue to use the results of measurements and extrapolation of autonomous sensors, or the rocket is redirected to the jammer. In the latter case, a direct guidance method is used.

If a decision is made about the ownership of the detected signal of an intercepted target, then the IVS meters go into automatic tracking of the target in range and direction, and the IVS is transferred to the mode of generating a mismatch (homing) parameter and forming a team to undermine the warhead of the rocket.

и

, а в угломерном канале 11 оценки углов

и приращений угловых скоростей

. Оценки

и

, а также рассчитываемые вычислителем автономной системы (АС) оценки

используются для формирования параметра рассогласования

, а оценки

- для вычисления параметров рассогласования

при методе наведения с постоянным углом упреждения.In this mode, estimates are generated in the rangefinder channel 10

and

, and in the goniometer channel 11 angle estimates

and increments of angular velocities

. Grades

and

as well as estimates calculated by the calculator of the autonomous system (AC)

used to form the mismatch parameter

, and estimates

- to calculate the mismatch parameters

with the guidance method with a constant lead angle.

If the rocket is guided by the algorithm in the form of an expression:

в горизонтальной плоскости и

в вертикальной, то в угломерном канале еще формируются оценки

поперечных ускорений цели. Знание оценки Д позволяет селектировать по дальности импульсы, отраженные от перехватываемой цели, путем отпирания приемника 4 отраженных сигналов только на время их прихода. Эта особенность позволяет повысить помехозащищенность ИВС в целом.

in the horizontal plane and

in the vertical, then in the goniometer channel estimates are still formed

lateral acceleration of the target. Knowing the estimate of D allows you to select the range of pulses reflected from the intercepted target by unlocking the receiver 4 of the reflected signals only for the time of their arrival. This feature allows to increase the noise immunity of the IVS as a whole.

The reference point for estimating the range is set by the TWS pulses arriving at the receiver 2 of the synchronization signals through the antenna 1.

.In space (direction), the target is selected due to the directional properties of the antenna 3 by rotating it in the direction determined by the estimates of the angles

.

, где

- оценка скорости, экстраполированной в автономной системе наведения ракеты. Поиск осуществляется путем изменения по линейному закону частоты специального гетеродина. При некотором значении этой частоты сигнал промежуточной частоты приемника отраженных сигналов (ПРМОС) попадает в узкополосный фильтр, после чего поиск прекращается и начинается этап обнаружения и анализа.With a continuous TWS, for the selection of signals reflected from the target, the Doppler frequency F _{rts is used} , which is proportional to the speed of approach of the rocket to the target. In a semi-active CWG, the frequency F _rc is distinguished as the frequency difference of two signals. One of them, reflected from the target, received by the antenna 3 A _os and amplified in the receiver 4 of the reflected signals, contains a Doppler frequency offset due to the speed of approach of the fighter with the target and target with the rocket. The second signal, u _c , received by antenna 1 and amplified by receiver 2, contains a Doppler frequency offset caused by the speed of the rocket moving away from the fighter. After subtracting the frequencies of the signals entering the receivers 4, 2 of the reflected and synchronizing signals, a signal is generated, the search and selection of which is performed in the processing module 5. With a range of D _p ≤ D _{s, the} search for this signal is carried out relative to the frequency F _tsu = 2V _tsu / λ, which is set by the target designation team V _tsu at the speed measured in the radar of the fighter. If D _p > D _{s the} search is performed relative to the frequency

where

- an estimate of the speed extrapolated to an autonomous missile guidance system. Search is carried out by changing according to the linear law of the frequency of a special local oscillator. At a certain value of this frequency, the signal of the intermediate frequency of the reflected signal receiver (PRMOS) enters the narrow-band filter, after which the search stops and the detection and analysis stage begins.

The selectable signal is analyzed for its belonging not only to the target or the jammer, but also to the Earth. This eliminates the capture and tracking of a signal reflected from the Earth, instead of a signal reflected from a low-flying target. The analysis is based on the energy and frequency differences of the signals emitted by the jammer and reflected from the Earth or from the target.

The decision on whether the detected signal belongs to the jammer leads to the same thing as when using pulsed signals, namely, if it is decided that the detected signal belongs to the Earth, a command is issued to resume the search for the target signal in frequency. When deciding whether the analyzed signal belongs to the intercepted target, the CWG meters go over to its automatic tracking according to the Doppler frequency performed by the auto-selector (channel 10 of estimation V _sat ) and in the direction carried out by the goniometer, and the CWG switches to homing mode.

The estimate formed by the auto-selector speed based on the measurement of the Doppler frequency F _rc , enters the calculator 6 mismatch parameters for the implementation of guidance methods. The goniometer channel 11 with a continuous TWS functions in the same way as with a pulsed signal with LF.

и скорости

. При этом Д оценивается по времени запаздывания отраженного сигнала, а скорость по частоте F_рц. Наличие информации о дальности позволяет повысить помехозащищенность РЭСУ за счет отпирания приемника только на время прихода сигналов, отраженных от цели.When using a quasi-continuous signal, the search and selection of the target are carried out both in range and in Doppler frequency. In the process of detecting a target, the same signal analysis takes place on its belonging to the jammer, the Earth or the target, as when using a continuous TWS. After the transition to automatic tracking of the target in range, speed and direction of the estimating device, D and V _Sat, form range estimates

and speed

. In this case, D is estimated by the delay time of the reflected signal, and the speed by frequency F _rts . The availability of information on the range allows to increase the noise immunity of the RESU due to the unlocking of the receiver only at the time of arrival of signals reflected from the target.

With a quasi-continuous TWS, it is necessary to eliminate the ambiguity of the range count, since the delay time of the reflected signal can exceed the pulse repetition period of the TWS. If it is impossible to ensure the uniqueness of the reference, the range is not estimated and tracking is not implemented. In such a situation, the reflected signal is selected not by range, but by the repetition period, which also allows the receiver to be gated for the time of arrival of the reflected pulses. The expediency of this technique is due to the fact that when calculating the mismatch parameters, knowledge of the current range is not required. The principle of operation of the goniometer channel 11 remains the same as when using TWS of other types.

и

, используемые при вычислении параметров рассогласования. Гироскопические датчики позволяют развязать антенну 3 РГС от угловых колебаний ракеты, что повышает точность и устойчивость сопровождения целей по направлению. Обработка исходной информации о дальности и угловом положении цели в вычислителе 13 позволяет получить дополнительную информацию о скорости и промахе ракеты относительно геометрического центра цели, а также о ее геометрических размерах. Рассмотрим схему сближения ракеты с целью (фиг.2).The self-motion parameters measuring instruments included in the system 7 of autonomous sensors (see FIG. 1), which primarily include accelerometers and gyroscopes, provide information on accelerations j _x and j _1,2 and pitch angles ν and yaw ψ. Based on the measurement of j _x and j _1,2 , estimates are formed in the calculators of the autonomous system

and

used in calculating the mismatch parameters. Gyroscopic sensors allow you to decouple the antenna 3 of the CWG from the angular oscillations of the rocket, which increases the accuracy and stability of target tracking in the direction. Processing the initial information about the range and angular position of the target in the calculator 13 allows you to get additional information about the speed and miss of the rocket relative to the geometric center of the target, as well as its geometric dimensions. Consider the rapprochement scheme of the rocket with the goal (figure 2).

According to figure 2, the coordinates of the target relative to the Z axis are indicated by discrete values Z ₁ , Z ₂ , Z ₃ , the current range values corresponding to the moment of passage of the target three fixed points, r ₁ , r ₂ , r ₃ and the current values of the angular position of the target is φ ₁ , φ ₂ , φ ₃ .

The geometric dimensions of the target are determined by measuring the distance to the target and the angular position of the starting and ending points on the target’s body.

The speed of approach of a rocket with a target is determined on the basis of fixing the time interval when the target passes two predetermined distances.

Missile missile relative to the target is determined based on the fixation of the current values of the range and angular position when the target passes three given distances.

A three-dimensional graph explaining the algorithm for determining miss missed relative to the target is shown in figure 3

According to figure 3, the location of the rocket (M) and target (T) at some point in time t will be:

where V _m , V _T - rocket speed and targets, respectively.

Then the distance r to the target can be calculated by the formula:

или

or

where V ² _c = V ² _T + V ² _m -2V _m V _T cosψ.

;

Then r ² = α ² Z ² + βZ + γ, where

;

In the special case, α, β, γ are constant.

For three different times:

and

Defining r ₄ as the limit at which Z = z ₄ = 0, we obtain:

Then, making the transformations, we get:

Missile missiles relative to the target can be represented as an expression:

- постоянные коэффициенты.Where

are constant coefficients.

The view of the target is determined based on information about the current range, the angular position of the target. Consider the rapprochement scheme of the rocket with the goal of figure 2

∠Ц ₁ О _r Ц ₄ = 90-φ _n ; ∠ОЦ ₄ Ц ₁ = γ = 180- [α + (90-φ)] = [90- (α-φ _n )]; ∠β = γ-90 ° = (γ _n -α)

for α ≠ n · π (n = 0,1)

Where

taking into account 1 and 2:

It can be seen from the figure that: ∠КЦ ₂ Ц ₁ = ∠β

∠KK ₁ 0 = ∠q = Θ-α.

Given 4 and 2, we have:

goal view:

The unit for fixing the current parameters of the target’s movement provides for fixing the current values of the range r ₁ , r ₂ , r ₃ relative to the given points of space, issuing a signal corresponding to the initial velocity of the expansion of fragments; as well as signals fixing the moments of passage of the target of the second and third predetermined distances. Input information is information about the range and angular position of the target.

Information about the current values of the range and the angular position of the target is supplied to the first and second input of the block 14 for fixing the current values of the parameters of motion of the target (figure 4). These signals through the functional converter 18, the first multiplier 19 are supplied to the first inputs of the first 20, second 21 and third 22 comparison devices, the second inputs of which receive signals from the first constant signal generator 26. When the set signals are exceeded, the signals from the outputs of the comparison devices exceed the first inputs of the first 23, second 24 and third 25 storage devices, the second inputs of which receive signals proportional to the current range to the target. Thus, the output of the first 23, second 24 and third 25 storage devices sequentially in time receives signals proportional to the current values of the ranges when the target passes fixed points of space (Z ₁ , Z ₂ , Z ₃ ) relative to the target (figure 2). In addition, the output of the second 21 and third 22 comparison devices receives a signal that determines the moment of passage of two fixed distances Z ₂ and Z _{3 by the} target, and from the fourth output of the constant signal generator 26, proportional to the initial velocity of the fragments V ₀ .

, который поступает на первый вход блока формирования команды на срабатывание боевой части ракеты (см. фиг.4).Block 15 missile missile determination based on incoming signals proportional to the value of r ₁ , r ₂ , r ₃ , forms a missile missile relative to the target (see Fig.6). These signals through the first 28, second 29 and third 30 quadrators are fed to the first inputs of the second 31, third 32 and fourth 33 multipliers, the outputs of which generate signals proportional to the values of A ² r ₁ ² , B ² r ₂ ² , C ² r, respectively _{March ^2.} These signals are input to the second functional converter 36 through the first 34 subtractor and second 35 adder. The output of the functional Converter 35 generates a signal proportional to the missile missile in the form of the expression:

, which is fed to the first input of the team formation unit for the operation of the warhead of the rocket (see figure 4).

Block 16 determine the geometric dimensions of the target generates a signal proportional to the geometric dimensions of the target. The input signals that ensure the functioning of the block 16 determine the geometric dimensions of the target are signals about the current range, the angular position of the target, as well as from the output of the receiver 4 reflected signals and signals that determine the moment of passage of the target two fixed distances Z ₂ , Z ₃ .

At the moment the target passes the second fixed distance, the signal from the fifth output of the block 14 for fixing the current parameters of the target’s movement Z ₂ enters the second input of the And 38 element, the first input of which receives the signal from the output of the receiver 4 of the reflected signals, in the presence of these signals from the output of the element 40 pulse generator. From the output of the pulse generator 40 through the shift register 42 and the DAC 43, the antenna control signal is supplied to the first input of the power amplifier 8 and the antenna drive. When this happens, the space is scanned in a given range (due to the operation of the key 12, the power amplifier 8 and the antenna drive are disconnected from the antenna control channel 11).

The initial values of the range and the angular position of the target are fixed at the moment the reflected signal from the target appears due to the operation of the third 44 and fifth 46 memory devices when a signal appears from the second output of the And 38 element.

The final values of the range and the angular position of the target are fixed at the moment the signal from the output of the receiver 4 of the reflected signals disappears due to the operation of the fourth 45 and sixth 47 memory devices when a signal appears from the output of the AND-NOT 39 element.

These signals from the outputs of the third 44 and fifth 46, fourth 45 and sixth 47 memory devices are supplied through the third 48 and fourth 49 quadrants, the third 50 totalizer to the first input of the second 51 subtractor, as well as through the third 52 subtractor, third 53 functional converter , the fifth 55 multiplier to the second input of the second subtracting device, the output of which is fed to the fourth 54 functional converter, which generates a signal in accordance with the expression

Block 17 determining the angle of the target based on the processing of input information about the current range and angular position of the target at discrete points in time, as well as information about the speed of approach and acceleration of the rocket determines the angle of the target. Discretization of input information about the current range and the angular position of the target is carried out by the second 74, third 75, fourth 76 and fifth 77 keys, which are controlled by the shift register 78, which is triggered by the pulse generator 79. From the output of the second and third keys, signals proportional to the values of r _n and r _{n + 1} are fed to the first inputs of the eighth 72 subtractor, sixth 59, and seventh 60 multipliers, respectively. From the output of the fourth 76 and fifth of 77 keys, signals proportional to the values of φ _n and φ _{n + 1} are received respectively at the first and second inputs of the ninth 73 subtractor. From the output of the ninth subtracter 73 a signal proportional to the value of Δφ = φ _n -φ _{n + 1} flows through the ninth and tenth 67 function generators 68 to the second input 59 of the sixth and seventh multipliers 60. From the output of the sixth 59 and seventh 60 multipliers, signals proportional to the values of r _{n + 1} cosΔφ and r _{n + 1} sinΔφ are received respectively at the second input of the eighth 72 subtractor and the second input of the second 62 divider, the first input of which receives the signal from the output of the eighth 72 subtractor, proportional to the value of r _n -r _{n + 1} cosΔφ. From the output of the second 62 divider through the eighth 66 functional converter, a signal proportional to the value of arcctg (r _n -r _{n + 1} cosΔφ / r _{n + 1} sinΔφ) is fed to the second inputs of the fifth 69 and seventh 71 subtracting devices. From the output of the seventh 71 subtractor, a signal proportional to the value β = φ _n -arcctg (r _n -r _{n + 1} cosΔφ / r _{n + 1} sinΔφ), through the sixth 64 functional converter is fed to the second input of the fifth 58 multiplier, the first input of which through the integrator 57 receives a signal proportional to the speed of the target. From the output of the fifth 58 multiplier, a signal proportional to the value of V _r sinβ is fed to the first input of the first 61 divider, to the second input of which from the sixth 70 of the subtractor a signal is proportional to the value of V _c . From the output of the first 61 divider through the fifth 63 functional converter, a signal proportional to the value of arcsin (V _r sinβ / V _c ) is fed to the first input of the fifth 69 subtractor, the output of which is fed to the seventh 65 functional converter, the output of which is a signal form of expression:

Block 18 forming a team to undermine the warhead of the rocket generates a signal to undermine the warhead of the rocket in accordance with the specific conditions of the approach of the rocket to the target and its geometric dimensions. The input information necessary for the functioning of this unit is information on the moment of passage of the target of the third fixed distance, on the approach speed, missile missile relative to the target, the initial velocity of the fragments, the geometric dimensions of the target and the angle of the target.

Information about the moment of passage of the target of the third fixed distance (Z ₃ ) and approach speed (V _sab. ), Miss missile (r ₄ ) and the initial velocity of fragmentation (V ₀ ) is received respectively through the third 80, fourth 81 dividers in the form of signals proportional to corresponding ratios Z ₃ / V _sb . and r ₄ / V ₀ , to the first and second inputs of the ninth 84 subtractor. The first input of the eighth multiplier receives a signal proportional to the ratio L _c / V _sb. , the second input of which, depending on the values of the angle of the target and the approach speed, receives a signal proportional to the ratio 1/2 or 2/3.

, на третий вход девятого 84 вычитающего устройства. В данном случае на выходе девятого 84 вычитающего устройства будет сформирован сигнал в виде выражения:If the current value of the target angle is greater than a certain value, then the fifth 88 comparator is triggered (the threshold is equal to the signal value at the first output of the fourth 96 constant signal generator), which ensures the triggering of the sixth 93 key. Then, from the second output of the fourth 96 constant signal generator, a signal proportional to the set value, through the sixth key 93, the fifth 88 summing device, is fed to the second input of the eighth 83 multiplier. The output of the multiplier 83 receives a signal proportional to the value

, to the third input of the ninth 84 subtractor. In this case, at the output of the ninth 84 subtractor, a signal will be generated in the form of the expression:

If the angle of the target and the approach speed are less than the specified value, then the second 89 and third 90 AND-NOT elements are triggered and, as a result, the third 92 And, eighth 95 keys are triggered.

In this case, the signal from the fifth output of the fourth 96 constant signal generator through the eighth 95 key, the second input of the fifth 86 summing device and the second input of the eighth 83 multiplier is fed to the third input of the ninth subtracting device. At the output of the ninth 84 subtractor, a signal will be generated in the form of the expression:

If the target’s angle is less than the set value, and the approach speed is greater than the set value, then the second 89 AND-NOTES are triggered, and, as a result, the first 91 AND elements, the seventh 94 key.

In this case, the signal from the fourth output of the fourth 96 constant signal generator through the seventh 94 key is fed to the second input of the fourth 85 summing device, the output of which will generate a signal in the form of the expression:

Thus, in addition to guiding the rocket, a team is formed to undermine the warhead of the rocket in accordance with the conditions of the rocket's approach to the target and the geometric dimensions of the target.

Information sources

1. Merkulov, V.N. Lepin. Aircraft radio control systems. Moscow. Radio and communications, 1997 - S.201 (prototype).

Claims (16)

1. The method of functioning of the information and computing system of the rocket, including preparing the rocket on board the carrier aircraft for operation, measuring the parameters of the target’s motion and the rocket’s own motion, forming an estimate of the necessary parameters of the relative motion of the target and the absolute motion of the rocket, choosing the method of guiding the rocket at the target, the best by any criterion for the given conditions of use, calculation for the selected method of the mismatch parameters characterizing the degree of mismatch of the actual param ditch of the rocket’s movement to their required values, analysis of the jamming situation and switching on the means of noise protection and non-radio measuring devices, depending on the jamming environment, redirecting the rocket to the jammer, generating a training and control signal for the radio fuse, characterized in that it is further determined based on the current values of the angular position and range to the target, the speed of approach of the rocket with the target in close proximity to it, missed missile, geometric dimensions and angle of the target, taking into account The low and initial flight speed of the fragments of the warhead of the rocket form a team to undermine the warhead of the rocket. 2. The method according to claim 1, characterized in that the rocket is prepared for work on board the carrier aircraft by supplying voltage from the fighter’s equipment, tuning the synchronization receivers and the reflected signal to the target’s illumination frequency, testing the operability of the entire rocket equipment, determining information readiness -the missile computing system to work on special control signals entering the fighter’s equipment through feedback circuits, preparing the meters and the computer to track the target, you rannoy to attack on command target designation. 3. The method according to claim 2, characterized in that the preparation of the meters and the calculator for tracking the target selected for destruction by targeting teams is carried out by rotating the homing antenna in the direction of the target or at the anticipated point where the target will be at the moment of capture it for auto tracking, execution of target designation commands for range and approach speed. 4. The method according to claim 3, characterized in that the target range commands are formed depending on the guidance method and the target illumination signal, while if a continuous target illumination signal is used in the homing radar, then the target designation command is formed according to the approach speed, according to which radio signals are selected only for that target, the approximation speed with which corresponds to the target designation speed, if a pulse target illumination signal is used in the homing radar, then a range targeting command is sent to the processing module, according to which the reflected signal receiver is unlocked only for the time of arrival of signals reflected from the target, which is distant from the fighter at a range of _Tsu , with a quasi-continuous target illumination signal, targeting commands are generated both in range and speed, at the same time, target designation commands for range, approach speed, and angular speeds of the line of sight are given as initial conditions to calculators that extrapolate the parameters of the relative motion of the rocket and ate in stand-alone mode information and computing missile system prior to the capture of the target on the trajectory, and in the case of exposure to the radio. 5. The method according to claim 1, characterized in that the analysis of the interference situation is carried out according to the energy and frequency differences of the signals emitted by the jammer and reflected from the ground or from the target, when deciding whether the analyzed signal belongs to the intercepted target, the radar homing meters go to its automatic tracking along the Doppler frequency performed by the auto-selector, and in the direction carried out by the goniometer, and translating the homing radar homing mode. 6. The method according to claim 1, characterized in that they determine the magnitude of miss missiles by mathematical expression

where A, B, C are constant coefficients, r ₁ r ₂ , r ₃ are the current distances recorded during the passage of the target three given distances Z ₁ , Z ₂ , Z ₃ . 7. The method according to claim 1, characterized in that they determine the speed of approach of the rocket with the target in the immediate vicinity of the target at the moment the target passes the second and third fixed distances from the mathematical expression

where Z ₂ , Z ₃ - the second and third fixed distances to the target, τ - the time interval during the passage of data of fixed distances. 8. The method according to claim 1, characterized in that the linear size of the target is determined at the moment it passes the second predetermined distance by scanning with its radiation pattern and fixing the angular positions and the distance to the starting and ending points on the target, respectively, at the time the reflected signal appears and disappears from mathematical expression goals

where D ₁ , D ₂ - the angular position of the start and, respectively, the end point on the target; Δφ = φ _H -φ _K is the angular size of the target. 9. The method according to claim 1, characterized in that they determine the angle of the goal by mathematical expression

where V _r , V _c are the modules of the rocket and target velocity vector, β is the angle between the components of the target vector, Δφ ₁ is the angular size between two fixed points relative to the rocket, r _n , r _{n + 1 are the} current values of the range to the target. 10. A device for operating a rocket information and computing system, comprising a serially connected antenna and a synchronization signal receiver, an antenna and a reflected signal receiver, an information processing module and a mismatch parameter calculator, as well as a system of autonomous sensors, a power amplifier and an antenna drive, the information processing module consists of a device for searching, detecting, selecting and analyzing signals, a channel for assessing the range and speed of approach, an antenna control channel, the output of which is mechanically connected to the reflected antenna, the output of the reflected signal receiver is connected to the first input of the information processing module, the second, third, fourth, fifth, sixth, seventh inputs of which are respectively connected to the first output of the synchronization signal receiver, the first and second outputs of the autonomous sensor system, with the exit of the training and target designation commands from the fighter equipment, which are simultaneously connected to the third input of the mismatch parameters calculator, with the output of the autonomous system calculator the first output of the power amplifier and the antenna drive, the second output of which is mechanically connected to the antenna of the reflected signal, while the first, second, third outputs of the information processing module are connected respectively to the input of the control and feedback signals of the fighter equipment, the first and second inputs of the mismatch parameters calculator wherein the second output of the synchronization receiver is connected to the second input of the reflected signal receiver, characterized in that it is provided with a first key and a formation calculator the command to detonate the warhead of the rocket, the first, second inputs of which are connected respectively to the first and second outputs of the information processing module, the third input is with the output of the reflected signal receiver, and the fourth input is with the second output of the autonomous sensor system, the first output is connected to the second input of the first key, the first input of which is connected to the second output of the antenna control channel, and the output of the first key is connected to the first input of the power amplifier and the antenna drive, the second input of which is connected to the second output, calculate I'm building a team at undermining warhead missiles, the third output which is the output of the command at undermining warhead missiles. 11. The device according to claim 10, characterized in that the calculator of the formation of the command to detonate the warhead of the rocket consists of a unit for fixing the current parameters of the target’s movement, a unit for determining miss missiles, a unit for determining the geometric dimensions of the target, a unit for determining the angle of the target and a unit for generating a command for detonating the missile’s warhead, the first, second, third and fourth inputs of the team formation calculator for undermining the rocket’s warhead are the first and second inputs of the block for fixing current parameters goal, block determining the geometric dimensions of the target, block determining the angle of the target, the fifth input of the block determining the geometric dimensions of the target and the fourth input of the block determining the angle of the target, the first, second, third, fourth, fifth and sixth outputs of the block fixing the current parameters of the target are connected respectively to the first , the second and third inputs of the missile miss detection unit, the second input of the command formation unit to detonate the missile’s warhead, the third input of the target's geometric dimensions, the third input the house of the team formation unit for undermining the warhead of the rocket and at the same time the fourth input of the missile defining unit; the output of the missile miss detection unit is connected to the first entrance of the team formation unit for disrupting the warhead of the missile, the first, second and third outputs of the unit for determining the geometric dimensions of the target are connected respectively with the second input of the power amplifier and the antenna drive, the fourth and fifth inputs of the team formation unit for undermining the warhead of the rocket, the fourth input of which is connected with the third input of the target angle determination unit, the output of which is connected to the sixth input of the command formation unit to detonate the missile warhead, the fifth output of the fixation unit of the current target movement parameters, the first output of the target geometrical size determination unit and the output of the command formation unit to detonate the missile warhead respectively, the first, second and third outputs of the calculator forming a team to undermine the warhead of the rocket. 12. The device according to claim 11, characterized in that the unit for fixing the current parameters of the target movement consists of a first functional converter, a first multiplier, a first, second and third comparing devices, first, second and third storage devices, as well as a constant signal generator, the first and second inputs of the unit for fixing the current parameters of the target’s movement are, respectively, the input of the first functional converter and the first inputs of the first, second, third storage devices, A, the second input of which is connected to the output of the first functional converter, and the output is connected to the first inputs of the first, second, and third comparing devices, the second inputs of which are connected respectively to the first, second, third outputs of the constant signal generator, and the outputs of the first, second, and third comparing devices are connected to the first inputs of the first, second and third storage devices, the outputs of which, as well as the output of the third comparing device and the fourth output of the first setter of constant signals als are respectively first, second, third, fourth and fifth current outputs fixing unit target motion parameters. 13. The device according to claim 11, characterized in that the missile miss detection unit consists of the first, second and third quadrators, second, third multipliers, the first subtracting and second summing devices, the second functional converter, as well as the second constant signal generator, and the first, second and third inputs of the missile miss miss determination block are respectively the inputs of the first, second and third quadrators, the outputs of which are connected respectively to the first inputs of the second, third and fourth smartly Iteli, the second inputs of which are connected respectively with the first, second and third outputs of the second constant signal generator, the outputs of the second, third and fourth multipliers are connected respectively with the first and second inputs of the first subtractor and the second input of the second summing device, the first input of which is connected to the output of the first subtracting device, and the output with the input of the second functional Converter, the output of which is the output of the missile miss detection unit. 14. The device according to claim 11, characterized in that the unit for determining the geometric dimensions of the target consists of a first element AND, a first AND element, a first pulse generator, a pulse counter and series-connected first shift register, digital-to-analog converter, and also from the third, the fourth, fifth and sixth storage devices, the third and fourth quadrators, the third adder, the second and third subtracting devices, the third and fourth functional converters, the fifth multiplier, the third a constant signal sensor, the first, second, third, fourth and fifth inputs of the unit for determining the geometric dimensions of the target are respectively the first inputs of the third and fourth, fifth and sixth storage devices, the second input of the first element And, the second input of the counter, the first input of the first element And and the input of the first element AND NOT, the output of the first element AND NOT connected to the second input of the first shift register and simultaneously with the second inputs of the fourth and sixth storage devices, the output of the first element And And connected to the input of the first pulse generator and simultaneously with the second inputs of the third and fifth memory devices, the output of the first pulse generator is connected to the first input of the first shift register and simultaneously with the first input of the pulse counter, n outputs of the first shift register are connected to n inputs of the digital-to-analog converter, the outputs of the third, fourth, fifth and sixth storage devices are connected respectively to the inputs of the third and fourth quadrators, the first and second inputs of the fourth reading device, in addition, the outputs of the third and fourth storage devices are connected to the first and second inputs of the fifth multiplier, the outputs of the third and fourth quadrants are connected to the first and second inputs of the third adder, the output of which is connected to the first input of the second subtractor, the output of the third subtractor is connected with the input of the third functional converter, the output of which is connected to the third input of the fifth multiplier, the fourth input of which is connected to the output of the third setter signals, and the output is connected to the second input of the second subtractor, the output of which is connected to the input of the fourth functional converter, the outputs of the digital-to-analog converter, counter, and fourth functional converter are the first, second, and third outputs of the unit for determining the geometric dimensions of the target, respectively. 15. The device according to claim 11, characterized in that the unit for determining the angle of the target consists of an integrator, sixth, seventh and eighth multipliers, first and second dividers, fifth, sixth, seventh, eighth, ninth and tenth functional converters, fifth, sixth , seventh, eighth and ninth subtracting devices, second, third, fourth and fifth keys, a second shift register and a second pulse generator, and the first, second, third and fourth inputs of the target angle determination unit are respectively the first and the inputs of the second and third, fourth and fifth keys, the first input of the sixth subtractor and the input of the integrator, the output of which is connected to the first inputs of the sixth multiplier and the second input of the sixth subtractor, the output of which is connected to the second input of the first divider, the first input of which is connected to the output the sixth multiplier, the second input of which is connected to the output of the sixth functional converter, the input of which is connected to the output of the seventh subtractor, the output of the first divider is connected to the input m of the fifth functional converter, the output of which is connected to the first input of the fifth subtractor, the second input of which is connected to the output of the eighth functional converter, the output of which is also connected to the second input of the seventh subtractor, the output of the fifth subtractor is connected to the input of the seventh functional converter, the outputs of the second, the third, fourth and fifth keys are connected respectively to the first inputs of the eighth subtractor, the seventh and simultaneously the eighth multipliers, the first and second inputs of the ninth subtractor, the first input of which is simultaneously connected to the first input of the seventh subtractor, the output of which is connected to the input of the sixth functional converter, the outputs of the seventh and eighth multipliers are connected respectively to the second inputs of the eighth subtractor and the second divider, the first input which is connected to the output of the eighth subtracting device, and the output to the input of the eighth functional converter, the output of the ninth subtracting device connected to the inputs of the ninth and tenth functional converters, the outputs of which are connected respectively to the second inputs of the seventh and eighth multipliers, the output of the second pulse generator is connected to the input of the second shift register, the first and second outputs of which are connected respectively to the second inputs of the fourth and second, fifth and third keys, the output of the seventh functional Converter is the output of the unit determining the angle of the target. 16. The device according to claim 11, characterized in that the unit for forming a command to detonate the warhead of a rocket consists of a third, fourth and fifth divider, a ninth multiplier, a ninth subtractor, a fourth and fifth summing device, a fourth and fifth comparing device, a second and the third AND elements, the second and third AND elements, the sixth, seventh and eighth keys, the fourth constant signal generator, the first, second, third, fourth, fifth and sixth inputs of the command formation unit for undermining the combat the rocket parts are respectively the first and second inputs of the fourth, third dividers, the first input of the fifth divider, the input of the fifth comparison device, in addition, the second input of the third divider is connected to the second input of the fifth divider and to the second input of the fourth comparison device, the outputs of the third, fourth and fifth dividers are connected respectively to the first, second inputs of the ninth subtractor and the first input of the ninth multiplier, the output of which is connected to the third input of the ninth subtractor devices, the first, second, third, fourth, fifth outputs of the fourth constant signal generator are connected respectively to the first inputs of the fifth and fourth comparing devices, the second inputs of the sixth, seventh and eighth keys, the outputs of the fourth and fifth comparing devices are connected respectively to the first inputs of the second AND element and the third AND gate, the sixth key and the second AND gate, the output of which is connected to the second input of the second AND element and the first input of the third AND element, the outputs of which, respectively connected to the first inputs of the seventh and eighth keys, the outputs of which are connected respectively to the second input of the fourth summing device and the second input of the fifth summing device, the first input of which is connected to the output of the sixth key, and the output to the second input of the ninth multiplier, the output of which is connected to the third input of the ninth a subtracting device, the output of which is connected to the first input of the fourth summing device, the output of which is the output of the command formation unit to undermine the warhead of the rocket.

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