RU2112699C1 - Method and device for control of flight of air-to-surface passive homing missile - Google Patents

Abstract

FIELD: rocketry; maintenance of target tracking point during entire self-contained flight of missile. SUBSTANCE: in course of self-contained flight, deviation of angles of turn of sight line in planes of control from their average magnitudes at present limited time interval is calculated on board missile in the special device by the present parameters of missile relative motion and point of tracking on target surface; then these deviations are compared with threshold values. In case one of them exceeds preset threshold value, this is indicative of reaming of homing head. In case of reaming, target tracking is discontinued and position of sight line is corrected to restore the initial position of tracking point. Upon completion of correction, target tracing is continued. In the course of correction, control of missile is effected by control signals calculated in device. EFFECT: enhanced efficiency of flight control. 5 cl, 3 dwg

Description

 The invention relates to the field of rocketry and can be used in control systems of aircraft missiles of the class "air surface".

 A known method of controlling the flight of a homing missile of the class "air - surface", which consists in pointing the rocket at a selected point on the target surface - the tracking point of the homing head (GOS) (and possible changes in the position of the tracking point in the process of autonomous flight is not controlled) by ensuring the movement of the rocket along the direction of the "launch point - tracking point" according to signals characterizing the relative motion of the rocket and the tracking point, in particular the angular velocities of the line of sight and bearings in the vertical and Horizontal planes measured GOS [1,2].

 From these sources of information, a device is known for implementing a method for controlling the flight of an air-to-surface homing missile, containing a homing head including a gyrostabilizer with a target coordinator installed on it, capturing the selected target before launching the missile, and an autopilot.

 A disadvantage of the known method and device is a sharp decrease in the efficiency of rocket flight control with an arbitrary change in the position of the target tracking point during an autonomous flight.

 A change in the position of the GPS tracking point during an autonomous flight leads to a negative result.

 When using the present invention, a technical result is achieved, which consists in ensuring that the initially selected missile maintains a tracking point on the surface of the target throughout the entire autonomous flight and thereby increases the efficiency of rocket flight control.

 To achieve the specified result in the known method of controlling the flight of a homing missile of the class "air - surface", which consists in ensuring the movement of the rocket in the direction of "launch point - tracking point" depending on the measured GOS in the vertical and horizontal planes of the values of the bearing angles or angular velocities of the line of sight , which in the process of processing information are converted into control signals by the gyro stabilizer of the seeker in the corresponding control channels, additionally in each control channel for a limited time interval, the gyrostabilizer determines the deviation angle of the gyrostabilizer from the mathematical expectation of its position in the previous time interval and compares it with two threshold values, exceeding the smaller of which means the beginning of the retargeting process, i.e., changing the position of the tracking point, and the larger one - the presence of redirection, requiring correction of the position of the gyro stabilizer homing; in this case, the rocket movement when the gyro stabilizer deviation angle is found within a larger threshold value is carried out using directly measured GOS parameters of the relative motion of the rocket and the tracking point, and when it exceeds a higher threshold value, the grip is removed, the GOS target capture is removed and the measurement of the parameters of the relative motion of the rocket and the tracking point is stopped , the position of the gyrostabilizer is adjusted by turning it in the direction of the aiming point, and at the end of the correction, Repeated capture of the target along the trajectory in the vicinity of the initially selected tracking point, while controlling the rocket during the correction period of the GYN gyrostabilizer (from the moment the capture was taken to its recovery) is performed using the calculated signals of the mathematical expectation of the angular velocities of the line of sight or the angles of the bearing in the vertical and horizontal planes in depending on the rocket control method before the start of correction.

 At the end of the correction, control is restored by the directly measured signals of the angular velocities of the line of sight or angles of the bearing.

 A particular case of the implementation of the present invention is such a control method in which to determine the value of the deviation angle of the GOS gyrostabilizer, the difference between the measured value of the gyrostabilizer control signal and its mathematical expectation calculated in the previous limited time interval is used.

 The technical result achieved by the implementation of the above method is achieved by using a device containing an autopilot and a homing head, including a target coordinator and a gyrostabilizer, the novelty of which is that it is equipped with a corrector that includes a threshold generation unit, a correction command generation unit ("Cor"), a unit for calculating the deviation angles of the gyrostabilizer, a unit for generating correction signals, a unit for generating control signals of a rocket during correction, a block for the command "Capture Resolution" ("RE") on the trajectory and the rocket control signal switching unit, and the gyro stabilizer control unit, into which the gyrostabilizer and the gyro stabilizer control signal switching unit are included, is introduced into the homing head, and one group of inputs of the threshold value generating unit is connected to command outputs of the autopilot, another group of its inputs with measuring outputs of the homing head and information outputs of the carrier, and outputs with the first group of inputs of the form block the Correction command and the first group of inputs of the gyro stabilizer deviation angle calculation unit, the other information inputs of which are connected to the information outputs of the target coordinator and the Correction command formation unit, and the outputs - to the second group of information inputs of the Correction command formation unit, command input which is connected to the output of the unit of formation of the command "RZ" on the trajectory, the command output of which is connected to the command inputs of the control unit gyrostabilizer and the formation of the team " RZ "on the trajectory, and the information outputs are connected to the inputs of the block for generating correction signals, one of the outputs of which is connected to the information input of the block for generating the RZ command on the trajectory, and the rest - with the first group of control inputs of the switching block of the gyro stabilizer control signals, the second group of control the inputs of which are connected to the outputs of the coordinator of the target, and the command inputs are connected to the outputs of the unit for generating the “РЗ” command on the path, and two groups of outputs are connected to two groups of inputs of the control unit a gyrostabilizer, the additional outputs of which are connected to the second group of inputs of the rocket control signal generation block during correction, and the main outputs are the outputs of the homing head and connected to the first group of inputs of the rocket control signal switching block, the second group of inputs of which is connected to the outputs of the rocket control signal generation block during correction, information and command inputs of which are connected to the corresponding outputs of the unit for forming the Correction command, commands the output of which is also connected to the input of the gyrostabilizer control unit and to the input of the “РЗ” command formation unit on a path whose outputs are connected to the command inputs of the rocket control signal switching unit, the outputs of which are connected to the autopilot.

 Separate inputs of the sides of the formation of the Correction command, the calculation of the deviation angles of the gyrostabilizer, the formation of correction signals and the formation of the RP command on the trajectory are connected to the timer.

 In FIG. 1 shows a block diagram of an air-to-surface homing missile flight control device; figure 2 is a graph illustrating possible variations in the calculated deviation angles of the gyrostabilizer and the corresponding cyclogram changes in the operation of the proposed device; figure 3 - comparative graphs with examples of changes in the position of the tracking point of the homing head during the autonomous flight of the rocket, the flight control of which is carried out in a manner known from the prototype and the method carried out according to the invention.

 A flight control device for a homing missile of the air-to-surface class (see FIG. 1) contains a homing head 1, which includes a target coordinator 2, a switching unit 3 of the gyrostabilizer control signals, a control unit 4 of the gyrostabilizer, a gyrostabilizer and a timer (not shown in the drawing ), autopilot 5, corrector 6, which includes a block for generating threshold values 7, a block for generating a command “Correction” 8, a block for calculating 9 angles of deviation of the gyrostabilizer, a block for generating correction signals 10, a block for generating Ia missile control signals for the correction 11, forming unit "RE" command on the path 12 and the switching control unit signals the missile 13.

; измерение угловой скорости линии визирования в горизонтальной плоскости

Координатор цели 2 применительно к заявленному устройству вырабатывает измеренные сигнал управления гиростабилизатором в вертикальной плоскости (СУ _y) и сигнал управления гиростабилизатором в горизонтальной плоскости (СУ _z).The homing head 1 in relation to the claimed device performs the following functions: measuring the bearing in a vertical plane (φ _{y g} ); bearing measurement in the horizontal plane (φ _{z g} ); measurement of the angular velocity of the line of sight in the vertical plane

; measurement of the angular velocity of the line of sight in the horizontal plane

The coordinator of the target 2 in relation to the claimed device generates the measured control signal of the gyrostabilizer in the vertical plane (CS _y ) and the control signal of the gyrostabilizer in the horizontal plane (CS _z ).

связаны с выходами головки самонаведения и подключены к соответствующим входам блока 13 переключения сигналов управления ракетой.The outputs of the coordinator of target 2 according to the specified parameters are connected to the inputs of the switching unit 3 of the gyrostabilizer control signals, the outputs of the block for generating correction signals 10 are connected to the others, by which a correction signal for the position of the gyrostabilizer in the vertical plane (SU _ycor ) and a correction signal for the position of the gyrostabilizer in the horizontal plane (SU _zkor ). The outputs of block 3 are connected to the inputs of the control unit gyrostabilizer 4, the outputs of which are signals

connected with the outputs of the homing head and connected to the corresponding inputs of the block 13 switching rocket control signals.

Autopilot 5 in relation to the proposed device performs the following functions: the formation of the commands "Ready", "Close guidance"("BN") and specified overloads in the control channels (n _ndI ) and (n _ndII ).

 The outputs of the autopilot 5 by the command signals "Ready" and "BN" are connected to the inputs of the block for generating threshold values 7, by the command "BN" - to the command input of the block 13 for switching rocket control signals.

The outputs of the autopilot according to the parameters n _assI and n _assII are the outputs of the device and are connected to the executive bodies of the rocket (not shown in the drawing).

The inputs of the block 7 the formation of threshold values for channels "DN-BN" - a method of controlling a missile and "CD-CB" - the target range is connected to the output of the carrier (not shown), and through the channels of the bearing angle in the vertical plane (φ _{y о} ) at the time of launch and the bearing angle in the horizontal plane at the time of launch (φ _{z о} ) - to the homing head 1. The outputs of the block for generating threshold values 7 along the channels of the duration of the integration interval (ΔT _int ), the threshold value of the calculated deviation angle of the gyrostabilizer, which determines its limiting ug The deviation due to natural interference (Δφ _{1 p} ), the threshold value of the calculated deviation angle of the gyrostabilizer, due to the permissible retargeting value (Δφ _{2 p} ), are connected to the corresponding inputs of the Correction command unit 8, the command input of which is by the Capture Resolution command ("РЗ") - to the corresponding output of the block 12 of the formation of the command "РЗ" on the trajectory, and according to the time of the beginning of the analysis of the gyrostabilizer control signals (t _on ) also to the block 9 for calculating the deviation angles ohm, to which the output of the duration of the calculation interval of the mathematical expectation of control signals of the gyrostabilizer (Δt _{m о} ) is also connected, and the second group of inputs of the unit for calculating 9 angles of deviation of the gyrostabilizer by the signals SU _y and SU _{z is} connected to the corresponding output of the coordinator of target 2.

 For time synchronization, blocks 8, 9, 10, 12 are connected to a timer (not shown in the drawing).

The outputs of block 8 according to the current mathematical expectation of the gyrostabilizer control signal in the vertical plane (mo _y ), the current mathematical expectation of the gyrostabilizer control signal in the horizontal plane (mo _z ), the calculated gyro stabilizer deviation angle in the vertical plane (Δφ _y ), the calculated gyro stabilizer deviation angle in the horizontal plane (Δφ _z) are connected to the 8 form a "correction" command corresponding inputs, outputs of which are prolonged by the value of the expectation gyrostabilizer control signal in the vertical plane (mo _simp) prolonged value expectation gyrostabilizer control signal in a horizontal plane (mo _zpr) connected to respective block 9 inputs 10, 11, the stored value of the calculated deflection angle gyrostabilizer in a vertical plane (Δφ _{y o)} and the stored value of the calculated deviation angle of the gyrostabilizer in the horizontal plane (Δφ _{z о} ) are connected to the correction signal generation block 10, the command inputs of the block numbers 9 of the gyro stabilizer deflection angles by the Correction command are connected to the command inputs of the correction signal generation block 10, the rocket control signal generation block 11 during correction and the RZ command generation block 12 on the trajectory.

The outputs of unit 10 are connected to the corresponding inputs of the gyro stabilizer control signal switching unit 3 by the control signal for correcting the position of the gyrostabilizer in the vertical plane (SU _ykor ) and the control signal for correcting the position of the gyrostabilizer in the horizontal plane (SU _ykor ). By the time the correction of the gyrostabilizer position is continued (t _cor ) - block 10 is connected at the corresponding input to block 12.

угловой скорости линии визирования при коррекции положения ГС в горизонтальной плоскости

угла пеленга в вертикальной плоскости (φ_{y кор}) и угла пеленга в горизонтальной плоскости (φ_{z кор}) соединены с соответствующими входами блока 13 переключения сигналов управления ракетой. Выходы блока 12 по командам "Разрешение захвата" ("РЗ") и "Снятие разрешения захвата" ("СРЗ") соединены с соответствующими командными входами блоков 3 и 13, дополнительный командный вход которого по командам "ДН - БН" соединен с соответствующим выходом носителя.The outputs of the block 11 formation of rocket control signals during correction by signals calculated by the angular velocity of the line of sight when correcting the position of the horizontal axis in the vertical plane

the angular velocity of the line of sight when correcting the position of the horizontal axis in the horizontal plane

the bearing angle in the vertical plane (φ _{y cor} ) and the bearing angle in the horizontal plane (φ _{z cor} ) are connected to the corresponding inputs of the rocket control signal switching unit 13. The outputs of block 12 by the commands “Capture Resolution” (“PZ”) and “Removal of Capture Resolution” (“SRZ”) are connected to the corresponding command inputs of blocks 3 and 13, the additional command input of which is connected to the corresponding output by commands “DN - BN” carrier.

The outputs of the coordinator of target 2 on the signals SU _y and SU _z in addition to block 9 are also connected to the corresponding inputs of the second group of inputs of block 3.

являются выходами головки самонаведения.Two groups of outputs of the unit 3 for switching the control signals of the gyrostabilizer according to the signals SU _ykor , SU _zkor , SU _y , SU _{z are} connected respectively to two groups of inputs of the gyrostabilizer 4, the outputs of which according to the signals

are the outputs of the homing head.

являются выходами корректора 6 и подключены к соответствующим входам автопилота 5.The outputs of block 13 by signals

are the outputs of the corrector 6 and are connected to the corresponding inputs of the autopilot 5.

и горизонтальной

плоскостях - команда "Ближнее наведение" ("БН"), из головки самонаведения 1 - о величине углов пеленга в вертикальной плоскости (φ_{y о}) и горизонтальной плоскости (φ_{z о}) на момент пуска, которые запоминаются по команде "Готов".Before launching the rocket, commands from the carrier are received to block 7 for forming threshold values, giving information about the range to the target "Long-range target"("CD") or "Short-range target"("CB"), the selected control method: at the angles of the bearing in vertical ( φ _{y g} ) and horizontal (φ _{z g} ) planes - the “Long-range guidance” (“NAM”) command or the angular velocities of the line of sight in the vertical

and horizontal

planes - the command "Close guidance"("BN"), from the homing head 1 - about the value of the angles of the bearing in the vertical plane (φ _{y о} ) and the horizontal plane (φ _{z о} ) at the time of launch, which are remembered by the command "Ready".

Based on the totality of the incoming information, the start time of the analysis, the duration of the interval, and the method for calculating the mathematical expectation of the gyrostabilizer control signals (Δt _{m о} ) and the integration interval (analysis cycle time) (ΔT _int ) are _selected , which can be corrected on the trajectory when changing the way the rocket moves from control at the angles of the bearing to control at the angular speeds of the line of sight (by the command "BN" coming from autopilot 5).

 After launch, the rocket is controlled by directly measured values of the angles of the bearing or angular velocities of the line of sight.

The block 8 of the formation of the Correction command and the block 9 for calculating the deviation angles of the gyrostabilizer are turned on at the moment t _at (see Fig. 2), determined in the block 7 for generating threshold values, and from that moment on, in block 9 in both control channels independently of each other the calculation of the current values of the mathematical expectation of the gyrostabilizer control signals mo _y , mo _z begins.

At the time t _{oy (z)} = t _by + Δ t _mo , the update of the current values of the mathematical expectation begins, while the calculation of the latter is performed on the time interval Δt _{m о} , shifted relative to the previous interval by the update step of the information received in the corrector 6.

Вычисленные значения сигналов Δφ_y и Δφ_z, а также текущее время с таймера поступают на блок 8 формирования команды "Коррекция", в котором независимо друг от друга сравниваются с порогом Δφ_п.
В случае, если величины Δφ_y и Δφ_z не превышают порогового значения Δφ_{1 п}, наведение ракеты происходит на выбранную перед пуском точку на поверхности цели, реакции корректора не требуется и управление ракетой осуществляется традиционным способом.At the same time, the calculation of the deviation angles of the gyrostabilizer from its average value by the formulas begins

The calculated values of the signals Δφ _y and Δφ _z , as well as the current time from the timer, are sent to the Correction command block 8, in which they are independently compared with the threshold Δφ _p .
If the values Δφ _y and Δφ _z do not exceed the threshold value Δφ _{1 p} , the missile is guided to a point selected on the target surface before launch, the corrector reaction is not required and the missile is controlled in the traditional way.

If one of the parameters Δφ _y or Δφ _z exceeds the threshold Δφ _{1 p} , which means the beginning of the redirection, the following operations are performed in the corrector (see figure 2).

The time for exceeding the threshold Δφ _{1 p} (t _1y or t _1z ) is _stored .

В канале, где не было отмечено превышения порога Δφ_{1 п} вычисление угла Δφ производится по формуле

Ситуация, при которой величина Δφ в течение интервала интегрирования ΔT_инт, начиная с момента превышения порога Δφ_{1 п}, не превысит пороговое значение Δφ_{2 п}, означает допустимое перенацеливание. В этом случае вмешательства корректора не требуется, ракета управляется традиционным способом. По окончании интервала ΔT_инт в блоке 9 производится обнуление величины Δφ в канале, где был превышен порог Δφ_{1 п}, и начинается новый цикл вычислений.From this moment, in the channel where the threshold Δφ _{1 p} was exceeded, in block 8, the calculation of the prolonged mathematical expectation of the gyrostabilizer control signal mo _{pr is} started by changing it in the previous time interval Δt _{m о} , in block 9, the gyro stabilizer deviation angle (Δφ) is calculated by the formula

In the channel, where the threshold Δφ _{1 p has} not been exceeded, the angle Δφ is calculated by the formula

The situation in which the Δφ value during the integration interval ΔT _int , starting from the moment the threshold Δφ _{1 p} is exceeded, does not exceed the threshold value Δφ _{2 p} , means an acceptable redirection. In this case, the intervention of the corrector is not required, the rocket is controlled in the traditional way. At the end of the interval ΔT _int in block 9, the value Δφ is zeroed in the channel where the threshold Δφ _{1 p} was exceeded, and a new cycle of calculations begins.

в блоке 4 управления гиростабилизатора формируются сигналы управления ракетой φ_{y кор} и φ_{z кор} и передаются в блок 11. В блоке 12 формирования команды "РЗ" на траектории формируется команда "Снятие РЗ", а в блоке 10 формирования сигналов коррекции формируются сигналы коррекции положений гиростабилизатора СУ_yкор, СУ_zкор по следующему алгоритму:

.A situation in which the Δφ value in the time interval ΔT <ΔT _int in one of the channels exceeds the threshold Δφ _{2 p} means a redirection requiring corrector intervention. In this case, when the threshold Δφ _{2 p} (t ₂ ) is exceeded, the Correction command block 8 generates a command according to which in the rocket control signal generation block 11 when corrected for the prolonged values of the mathematical expectation of the gyrostabilizer control signals (mo _zpr and mo _ypr ) rocket control signals are formed

in the gyrostabilizer control unit 4, the rocket control signals φ _{y cor} and φ _{z cor} are generated and transmitted to block 11. In the block 12 for generating the “РЗ” command, the command “РЗ Removal" is generated on the trajectory, and in block 10 for generating correction signals, position correction signals are generated gyrostabilizer SU _ykor , SU _zkor according to the following algorithm:

.

The correction signals SU _core and SU _core arrive at block 3 switching control signals of the gyrostabilizer during the correction time, i.e. from the moment of receipt from the block 12 of the command "SRZ" to the end of the interval t _cor .

на сформированные в блоке 11

. При отсутствии команды "БН" (наличии команды "ДН") управление ракетой производится по соответствующим углам пеленга φ_{y г} и φ_{z г} или φ_{y кор} и φ_{z кор}. .The SRZ command from block 12 also enters the rocket control signal switching block 13, where, with the BN command, the rocket control signals are switched from the measured

formed in block 11

. In the absence of the “BN” command (the presence of the “DN” command), the missile is controlled at the corresponding bearing angles φ _{y g} and φ _{z g} or φ _{y cor} and φ _{z cor} . .

на сигналы

или с сигналов φ_{y кор} , φ_{z кор} на сигналы φ_{y г} , φ_{z г}, , а в блоке 8 начинается новый цикл анализа.At the end of the correction time in block 12, an RZ command is generated, according to which in block 3 the gyrostabilizer control is switched from the correction signals SU _ykor and SU _zkor to the measured control signals SU _y , SU _z , in block 13 the rocket control is switched from signals

on signals

or from signals φ _{y cor} , φ _{z cor} to signals φ _{y g} , φ _{z g} , and in block 8 a new analysis cycle begins.

Figure 3 presents a fragment of a large-sized target, on which point A is applied - the initially selected tracking point, point B is the changed tracking point when Δφ _y reaches the threshold φ _{2 p} , point C is the position of the tracking point after correction of the gyrostabilizer position.

 In the case of traditional control of the gyrostabilizer position (prototype), the position of the tracking point can change arbitrarily, including going beyond the target's contour (point D).

 Calculations and experiments show that the proposed method for controlling an air-to-surface missile allows the missile to be guided to the initially selected target area for the entire duration of the flight and thereby significantly increase the efficiency of missile flight control.

Claims (5)

 1. The method of controlling the flight of an air-to-surface missile with passive homing, namely, that a tracking point is selected on the target surface, during the autonomous flight, the parameters of the relative motion of the rocket and the tracking point on the target surface are measured and the rocket moves in the direction " launch point - tracking point "depending on the measured parameters, characterized in that during the autonomous flight of the rocket control the position of the tracking point by determining the magnitude of the current deviation its position from the one selected before launch and comparing this value with a threshold value, in this case, if the deviation value is within the specified threshold value, the rocket movement is carried out depending on the measured parameters of the relative motion of the rocket and the tracking point, and if the deviation value is outside the specified threshold value, stop the measurement of the parameters of the relative motion of the rocket and the tracking point, forcibly restore the original position of the tracking point and resume the measurement process, while the movement of the rocket during the absence of the measured parameters of the relative motion of the rocket and the tracking point is carried out according to the calculated control signals.  2. The method according to claim 1, characterized in that the angular velocities of the line of sight and the angles of the bearing in the vertical and horizontal planes are used as parameters of the relative motion of the rocket and the tracking point on the surface of the target.  3. The method according to claim 1, characterized in that as the parameters characterizing the current deviation of the tracking point, use the deviation angles of the line of sight in the vertical and horizontal planes from their average value for a limited current time interval.  4. The method according to claim 1, characterized in that the calculated control signals use the mathematical expectation of the angular velocity of the line of sight in the vertical and horizontal planes or the bearing angles in the vertical and horizontal planes, memorized at the time of the start of the redirection.  5. A flight control device for an air-to-surface rocket with passive homing, containing an autopilot and homing head, including a target coordinator and a gyrostabilizer, characterized in that it is equipped with a corrector including a threshold generation unit, a Correction command generation unit, a unit calculating the deviation angles of the gyrostabilizer, a block for generating correction signals, a block for generating signals for rocket control during correction, a block for generating the command "Capture Resolution" on the trajectory and a rocket control signal switching unit, and a gyrostabilizer control unit, into which the gyrostabilizer is included, and a gyrostabilizer control signal switching unit, and one group of inputs of the threshold formation unit is connected to the autopilot command outputs, the other group of its inputs to measurement outputs is introduced into the homing head homing heads and information outputs of the medium, and outputs with the first group of inputs of the Correction command formation block and the first group of inputs of the block calculating the deviation angles of the gyrostabilizer, the other information inputs of which are connected to the information outputs of the target coordinator and the Correction team formation unit, and the outputs - to the second group of information inputs of the Correction team formation unit, the command input of which is connected to the output of the command formation unit of Capture Resolution "on the trajectory, the command output of the Correction command formation unit is connected to the command inputs of the gyrostabilizer control unit and the" Resolution "command formation unit capture "on the trajectory, and the information outputs are connected to the inputs of the correction signal generation block, one of the outputs of which is connected to the information input of the capture resolution command generation block on the trajectory, and the rest with the first group of control inputs of the gyro stabilizer control signal switching block, the second group the control inputs of which are connected to the outputs of the coordinator of the target, and the command inputs are connected to the outputs of the unit for generating the command “Capture Resolution” on the trajectory, and two groups of outputs are connected with two groups of inputs of the gyrostabilizer control unit, the additional outputs of which are connected to the second group of inputs of the rocket control signals generation unit during correction, and the main outputs are the outputs of the homing head and connected to the first group of inputs of the rocket control signals switching block, the second group of inputs of which is connected to the outputs of the unit for generating rocket control signals during correction, the information and command inputs of which are connected to the corresponding outputs of the pho block the formation of the Correction command, the command output of which is also connected to the input of the gyrostabilizer control unit and the input of the Capture Resolution command generation unit on the path, the outputs of which are connected to the command inputs of the rocket control signal switching unit, the outputs of which are connected to the autopilot, separate inputs of the formation units Correction commands, calculating the gyro stabilizer deviation angles, generating correction signals and generating the Capture Resolution command on the path are connected to the timer .

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