RU2253821C1 - Firing section - Google Patents

Abstract

FIELD: defense-equipment, in particular, mobile antiaircraft guided missile systems, in which the antiaircraft guided missiles are guided with the aid of semiactive or active radar homing heads, applicable for organization of antiaircraft defense of troops and military objects against destruction by the aids of potential enemy air attack.

SUBSTANCE: the firing section has an installation with a guidance and illumination radar consisting of a device of target illumination, navigation, topographical survey and orientation system, digital computer system, multifunctional radar, take-off automatic equipment, and an antiaircraft guided missile including an on-board digital computer, transceiving antenna, radio transmitting device of the active radar homing head, modulating pulse shaper, radio-receiving device of the active homing head, autopilot, missile control surfaces control unit. The novelty in the claimed firing section is in the fact that the installation with a guidance and illumination radar uses a direction finder at the frequency of the active homing head, optimum detecting filter and a former of the radiation cut-off commands, and the antiaircraft guided missile uses a radio-receiving device for receiving the telecontrol commands at the frequency of illumination and a former of the commands of variation of the modulation parameters.

EFFECT: enhanced probability of lock-on of the target signal by the active radar homing head, reduced duration of firing section radar contact with the target and non-destruction of it by antiradar missiles.

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Description

The alleged invention relates to defense technology, in particular to mobile anti-aircraft missile systems (SAM), in which anti-aircraft guided missiles (SAM) are guided with the help of semi-active or active radar homing heads (RGS), and can be used to organize air defense (air defense) troops and military installations from defeat by means of an air attack (IOS) of a potential enemy.

In the structure of modern anti-aircraft defense, the fire section is the main and almost the only means for organizing the launch and guidance of missiles at the air defense system.

Firing sections are known, for example, of the American Patriot SAM, including a combat control point (PBU), a multifunctional radar station (IFRS), launchers (PU), each of which has N ready-to-launch missiles. The number of launchers in the firing section may be different [see F.K. Neupokoev. Shooting anti-aircraft missiles. M., Military publishing house M.O. USSR, 1980, p. 53; A.S. Malgin. Fire control anti-aircraft missile systems. M., Military Publishing House, 1987, p.21].

In the firing section of the Patriot air defense missile system, the whole type of remote control missile system (before meeting the missile with the target) was implemented before the capture of the target signal of the semi-active CWS of the second type telecontrol command system (TU-11), therefore the MFRS provides information reception along with the tasks to accompany the fired target from onboard coordinators of missiles, as well as recalculation of the current coordinates of the target relative to the standing point of the air defense system [V.P. Demidov, N.Sh. Kutyrev. Anti-aircraft missile control. M., Military Publishing House, 1989, p. 295]. This leads to the fact that the time of the radar contact of the MFRS of the fire section with the target becomes comparable with the time of flight of the missile to the target, which can be more than 70-80 s, which is quite enough to bombard the radiating means of the fire section with anti-radar missiles (PRR).

There are also options for combat sections in which the functions of IFRS and missile launchers for launching missiles with semi-active or active CSGs are structurally combined [Russian Arms, 2001 ... 2002, M., Military Parade, 2001, Self-propelled fire system ( SOU) 9A310 M1-2, which is part of the Buk-M1-2 air defense system, pages 570 ... 571; EI No. 13, 2003, p. 5 (Jane's Defense Weekly, 5, II, 2003, p.6) ... missile launcher “Derby” with an active CSG], as well as fire sections that do not contain PBUs, and consisting only of IFRS and launchers with missiles. Such fire sections include a section or a fire platoon included in the Advanced KHOK air defense system [see N.Ya. Vasilin, A.A. Gurinovich. Anti-aircraft missile systems. Mn., LLC “Popuri”, 2002, p. 421].

The fire sections of the Buk-M1-2 and Advanced Khok air defense missile systems have the same drawback as the Patriot air defense section, since after launching a SAM with a semi-active anti-aircraft missile at the frequency of the target illumination transmitter, radio correction commands are continuously transmitted to the SAM surface (RK) produced by the digital computer system (CVS) of the MFRS accompanying the fired target to the point of meeting the missiles with the target. The time duration of the radar contact of the MFRS of the fire section with the target reaches 70 s, which does not allow to achieve the necessary value of the probability of non-damage of the radiating means of the fire section by anti-radar missiles. In the fire section of the Derby air defense system, the capture of the target signal of an active CWG is carried out mainly before the launch of the SAM. In this case, the firing of low-flying targets (NLC), i.e. targets whose current elevation angle is less than the half-width of the antenna pattern (BOTTOM) of the active CWG will be realized under conditions of powerful reflections from closely spaced objects and parts of the underlying surface, which can lead to active repetition of pulses at high repetition frequencies (for short strobe pulses) CWG to overload or roughen the receiving device. In addition, the use of the target signal capture mode on the launcher leads, respectively, to a decrease in the far boundary of the affected area.

The use of the “target signal capture in air” mode, which is also provided for in the Derby air defense system, imposes increased requirements on the accuracy of target designation from MFRS to SAM and on the accuracy of launching the launcher in the direction of the anticipated meeting point. In this case, the real trajectory of the SAM, especially at the initial moment of uncontrolled guidance, will differ from the kinematic one due to the impact of various disturbances on the control system (instrumental errors, inertia, etc.), which reduces the probability of capturing the target signal by an active CWG.

The closest in technical essence is the firing section of the Buk-M1-2 air defense system (SOU 9A310M1-2). It consists of an installation with a radar for illumination and guidance as part of a multifunctional radar station with a recognition system, a transmitting device for illuminating the target and transmitting radio correction commands to the anti-aircraft guided missile, a digital computer system, navigation, topographic and orientation systems, starting automation equipment and an anti-aircraft launcher guided missiles in the radio receiver of the active radar homing head, on-board digital computing th car transceiver antenna, a radio transmission apparatus, an active radar seeker, a modulator (modulating or pulse generator), a radio receiver radio correction commands, autopilot control device rudders missiles.

The disadvantage of this prototype is the inability to adjust or change the trajectory of an anti-aircraft guided missile with an active homing radar in the initial phase of flight, which reduces the likelihood of target capture due to the impact of various disturbances on the system.

The technical result of the invention is to increase the likelihood of capturing the target signal by an active homing radar while reducing the duration of the radar contact of the firing section with the aim and not to damage it with anti-radar missiles.

The essence of the invention lies in the fact that the firing section contains an installation with a radar of guidance and illumination, consisting of a target illumination device, a navigation system, topographic location and orientation, a digital computer system, a multifunctional radar station, and automation equipment. The output of the digital computer system is connected via a bus to the first input of the target illumination device. The first input-output of the digital computing system is connected to the input-output of the starting automation equipment. The second input-output of the digital computer is connected to the input-output of the multifunctional radar station, the output of the navigation, topographic and orientation systems is connected by a bus to the first input of the digital computer system. An anti-aircraft guided missile consists of an on-board digital computer, a transceiver antenna, a radio transmitter of an active radar homing head, a pulse shaper, a radio receiver of an active homing head, an autopilot, and a rudder control device. The first input-output of the on-board digital computer is connected to the second input-output of the starting automation equipment, the second input-output of the on-board digital computer is connected to the input-output of the transceiver antenna. The second output of the on-board digital computer is connected to the first input of the autopilot, the output of the autopilot is connected to the input of the rocket rudder control device, the output of the rocket rudder control device is connected to the second input of the autopilot. The input of the radio receiver of the homing radar is connected to the output of the transceiver antenna, and the output of the radio receiver of the active radar homing head is connected to the first input of the on-board digital computer, the output of the modulating pulse generator is connected to the input of the radio transmitter of the active homing head, the output of which is connected to the transceiving antenna. New features of the claimed fire section is that a direction finder at the frequency of the active homing head, an optimal filter and a shaper of commands to turn off the radiation are introduced into the installation with a radar for illumination and guidance. The first output of the direction finder at the frequency of the active homing head is connected to the optimal filter and the radiation shutter command shaper connected in series, the first output of the radiation shutdown command shaper is connected to the input of the multifunctional radar station. The second output of the radiation shutdown command generator is connected to the input of the target illumination device, the second output of the direction finder at the frequency of the active homing head is connected to the second input of the digital computer system by the bus. A radio receiving device for receiving telecontrol commands at the backlight frequency and a shaper of modulating modulation parameters are introduced into the anti-aircraft guided missile. The output of the radio receiving device for receiving telecommand commands at the backlight frequency is connected to the second input of the on-board digital computer, the first output of the on-board computer is connected to the input of the shaper of the modulation parameters, the output of which is connected to the input of the modulating pulse generator.

The drawing shows a functional diagram of the fire section.

The firing section consists of a unit with a radar for illumination and guidance 1 and an anti-aircraft guided missile 2. Installation with a radar for illumination and guidance 1 contains a direction finder at the frequency of the active homing 3, an optimal filter 4, a shaper of the command to turn off radiation 5, a device for illuminating the target 6, a navigation system , topographic location and orientation 7, digital computing system 8, multifunctional radar station 9, starting automation equipment 10. Anti-aircraft guided missile 2 consists of a radio receiver about the device active radar homing 11, on-board digital computer 12, the shaper commands change modulation parameters 13, the transceiver antenna 14, the radio transmitting device active radar homing 15, the shaper modulating pulses 16, the radio receiving device for receiving telecontrol commands at the backlight frequency 17, autopilot 18 rocket rudder controls 19.

The first output of the direction finder at the frequency of the active homing head 3 is connected to the optimal filter 4 connected to the shaper of the radiation shutdown command 5. The first output of the shaper of the radiation shutdown command 5 is connected to the input of the multifunction radar station 9. The input-output of the multifunction radar station 9 is connected to the second input the output of the digital computing system 8. The first input-output of the digital computing system 8 is connected to the first input-output of the equipment of the starting av Tomatics 10. The output of the digital computer system 8 is connected via a bus to the first input of the target illumination device 6, the second input of the target illumination device is connected to the second output of the radiation shutdown command generator 5. The second output of the direction finder at the frequency of the active homing 3 is connected by bus to the second input of the digital computer 8, the first input of the digital computer 8 is connected via a bus to the output of the navigation and topographic location 7. The second input-output of the starting automation equipment 10 is connected to the first input go on-board digital computer 12, the first output of the on-board computer 12 is connected to a series-connected modulator 13 modulator, modulating pulse generator 16, the active transmitter homing 15 and the transceiver antenna 14. The second output of the on-board computer 12 is connected to the first input autopilot 18, the output of autopilot 18 is connected to the input of the rudder control device 19, the output of the rudder control device 19 is connected to the second input of the autopilot 18. The second input-output of the on-board digital computer 12 is connected to the input-output of the transceiver antenna 14, the output of the transceiver antenna 14 is connected to the input of the radio receiver of the active homing 11. The output of the radio receiver of the active homing 11 is connected to the first input of the digital onboard computer 12. The output of the radio receiving device for receiving telecommands at the backlight frequency 17 is connected to the second input of the on-board digital computers s 12.

In the drawing are indicated:

r _TU , r _tu ^(input) - signal level at the output of the target illumination device 6 carrying the telecontrol command and, accordingly, at the input of the radio receiver of the telecontrol command at the backlight frequency 17;

p _ARGS , R _ARGS ^(p) - signal level at the output of a SAM transceiver antenna with an active CGS and, accordingly, at the direction finder input at the frequency of the active homing head 3, which is part of the installation with a radar of guidance and illumination;

p _radar , p _C ^(radar) - the signal level at the output of the multifunctional radar station and the signal level of the target at the input of the multifunctional radar station, respectively;

R _C ^(A) - the signal level of the target at the input of missiles with an active radar homing.

The fire section works as follows.

After installing the fire equipment of the fire section at positions from the navigation and topographic location system (7) of the installation with a guidance and illumination radar (URNP), the values of the current X and Y coordinates are entered into the digital computer system (8). Information about the coordinates of the detected target “C” in the radial coordinate system from the multifunctional radar station (9) is also transmitted to the digital computer system (8), in which the calculation of the pointing angles φ _{a nav} and φ _{N nav} (where α _{a nav} and φ _{N nav} - the angular coordinates of the target in the azimuthal and elevation planes, respectively) for the transceiver antenna (14) and the determination of the coordinates of the anticipated or instantaneous meeting point of the anti-aircraft guided missile with the target depending on its parameters. Data on the angular coordinates of the anticipated or instantaneous meeting point of the anti-aircraft guided missile (SAM) with the purpose of using to direct the missiles located on the launcher in the desired direction. At the same time, it is assumed that the parallel approach method is used to direct the SAM, since in comparison with other methods when using it, the least demands are made on the maneuverability of an anti-aircraft guided missile.

With the method of parallel approach during the entire flight of missiles to an anticipated or instantaneous meeting point, the missile-target line remains parallel to this direction if one of the following three conditions is met:

where V _c , V _p - target speed and missiles, respectively;

q _C is the angle between the line of sight of the target missile and the target velocity vector;

q _p is the angle between the missile target line and the rocket velocity vector;

- угловая скорость вращения линии ракета-цель;

- angular velocity of rotation of the missile-target line;

ε _d0 - the angle of inclination of the missile-target line at the time of the start of guidance

[V.P. Demidov, N.Sh. Kutyrev. Anti-aircraft missile control. M., Military Publishing House, 1989, p.27].

After the escorted target has entered the affected area, and if there is information about the firing or the possibility of firing at the fire section with anti-radar missiles, an anti-aircraft guided missile is launched with an active homing radar.

To exclude the influence of reflections of the probe signal from the underlying surface and closely spaced objects during the firing of low-flying targets (NLC) on the radio receiver of the active homing radar 11, the SAM is launched with the capture of the target signal in speed (Doppler frequency) and angular coordinates in the air (“ ЗВ ”), i.e. when the RPDU (15) is turned on at the launch site.

After the launch site is over, tracking of missiles by a direction finder begins at the frequency of the active homing head (3) at the radiation frequency of the active radar homing head [L.S. Belyavsky, B.C. Novikov, P.V. Olyanjuk. The basics of radio navigation. M .: Transport, 1982, p. 90]. The radio transmitting device of the active homing radar (15) also reaches its nominal mode during the launch phase. In the process of tracking an anti-aircraft guided missile with a direction finder at the frequency of the active homing head (3), its actual angular coordinates and the distance from the installation with a radar taken (or calculated) from a mathematical model of guiding the anti-aircraft guided missile to an anticipated or instantaneous meeting point are continuously compared with the kinematic parameters trajectory computed by a digital computing system (8). In this case, the parameters of the kinematic trajectory at each specific moment in time are refined (or changed) taking into account the possible maneuver of the target. If an anti-aircraft guided missile with an active homing radar after completing the launch site does not capture the target signal, an “accumulation” of the error path starts, which leads to the appearance (appearance) of an initial mismatch in the flight path of the anti-aircraft guided missile in the general case in angular coordinates in two planes.

With the appearance of “mismatch”, the “output” section begins using the telecontrol mode of the first type, in which the telecommands generated by the digital computer system (8) are transmitted to the input of the radio receiver telecontrol commands at the backlight frequency using the target illumination device (6) (17) ) anti-aircraft guided missiles with active radar homing. Telecontrol commands are formed on the basis of information about the current angular coordinates and the distance to the missile (ε _p , D _p ) and the target (ε _c , D _c ), proportional to the error signal Δε, which is transmitted on board the anti-aircraft guided missile. From the output of the radio receiving device for receiving telecontrol commands at the backlight frequency (17) through the on-board digital computer (12), the control commands enter the autopilot (18), after which the stage of processing the initial error in the spatial position of the SAM or its velocity vector (i.e. initial error of the control parameter).

In the general case, with the available or specified parameters of the control loop and flight-ballistic characteristics of the anti-aircraft guided missile, the time, and therefore the range of its withdrawal to the guidance path, is a random variable, which depends mainly on the initial shooting error (which includes target designation errors) of the missile a given amount of space near the kinematic trajectory and the angular velocity of the line of sight of the target (the magnitude of this speed determines the curvature of the desired trajectory in the output section). At the same time, it can be considered that in each guidance plane the dispersion of the position points of the anti-aircraft guided missile at the time the telecontrol begins is independent and subject to the normal law [F.K. Neupokoev Anti-aircraft missile firing. M., Military publishing house M.O. USSR, 1980, p. 238].

After the initial mismatch at the site of launching the missile launcher onto the necessary trajectory (close to the kinetic or in the region of permissible mismatches with the parallel approach method) using telecontrol is reduced to acceptable values, the signal level at the frequency of the radio transmitting device of the active homing radar (15), reflected from the target, at the input of the radio receiver of the active radar homing head (11) becomes sufficient for its capture. After the “additional search” for Doppler frequency shift (capture of the target signal by speed) and capture of it by angular coordinates in the on-board digital computer (12), the “capture” command is generated, which, in addition to solving the main tasks associated with pointing missiles at a proactive or instantaneous point meeting, is fed to the input of the command shaper to change modulation parameters (13) of the formation of the team to change the duration τ and the repetition period T of the probe pulses [B.A. Kalabekov, I.A. Mamzelev. Digital devices and microprocessor systems. M.: Radio and communications, 1987 p. 59 ... 62]. Next, this command is fed to the input of the modulating pulse shaper (16), where the change of τ and T is carried out while maintaining the duty cycle, i.e.

T ₁ , τ ₁ is the repetition period and duration of the pulses of the active radar homing head (15) emitted by the radio transmitting device at the initial pointing moment;

T ₂ , τ ₂ - respectively, the repetition period and the duration of the pulse after the capture of the target signal by the active radar homing head.

In this case, in order to reduce the “dead” zone in range, it is advisable to change “T” and “τ” in the direction of their decrease compared to the initial values, when the distance “anti-aircraft guided missile - target” is still significant.

Radiated by the side lobes of the transceiver antenna (14), the signal is fed to the direction finder input at the frequency of the active homing head (3) and then from its output to the input of the optimal filter (4) to process the pulse sequence with known parameters [M.I. Finkelshtein. Basics of radar. M .: Sov. Radio, 1973, p. 208].

As soon as an impulse sequence with T ₂ and τ ₂ appears at the input of the optimal filter (4), a signal appears at its output, which is then fed to the shaper of the radiation shutdown command (5), and from the first output of the shaper of the radiation shutdown command (5), goes to turn off the radiation of the multifunctional radar station (9), and from the second output - to turn off the target illumination device (6). From that moment on, an anti-aircraft guided missile with an active homing radar goes completely into autonomous guidance on the target, and the firing section, in the event of a possible firing of anti-radar missiles after 40 ... 50 s, can begin to fire at a new target according to the adopted target designation. The time of the radar contact of the fire section with the target is 20 ... 25 s.

If the trajectory parameters (or aiming errors) are within acceptable limits immediately after the completion of the launch phase and the inclusion (reaching the nominal mode) of the radio transmitting device of the active homing radar (15), the active homing radar captures the target signal, the shaper of commands for changing modulation parameters (13 ) forms a command to change the values of “T” and “τ”. The pulse sequence with the new values of T and τ through the direction finder at the frequency of the active homing head (3) is fed to the optimal filter (4), after which the transmitting devices of the multifunction radar station (9) and the device are turned off by the output of the command shaper to turn off the radiation (5) target illumination (6). Anti-aircraft guided missile goes into autonomous homing without turning on the telecontrol loop, and the time of the radar contact of the fire section with the goal is reduced to the reaction time of the fire section (up to 20 s).

Thus, in the proposed fire section, the duration of the radar contact of the fire section with the target decreased by 2.5 ... 3 times, the likelihood of capturing the target signal by the active homing radar increased. Additional advantages of the proposed technical solution include the fact that the radiation from the illumination device at known frequencies at the initial moment after the launch of an anti-aircraft guided missile creates the appearance of launching an anti-aircraft guided missile with a semi-active homing method, which introduces disinformation to a potential enemy for a certain amount of time.

Claims (1)

The firing section, containing the installation with a guidance and illumination radar, consisting of a target illumination device, a navigation system, topographic location and orientation, a digital computer system, a multifunctional radar station, starting automation equipment, the output of the digital computer system being connected via a bus to the first input of the target illumination device, the first input-output of the digital computer system is connected to the input-output of the starting automation equipment, the second input-output of the digital computer s is connected to the input-output of a multifunctional radar station, the output of the navigation, topographic and orientation system is connected by a bus to the first input of a digital computer system, an anti-aircraft guided missile consisting of an on-board digital computer, a transceiver antenna, a radio transmitting device for an active homing radar, a modulating pulse generator , a radio receiver of the active homing head, autopilot, rocket rudder control device, wherein the first input-output of the on-board digital computer is connected to the second input-output of the starting automation equipment, the second input-output of the on-board digital computer is connected to the input-output of the transceiver antenna, the second output of the on-board digital computer is connected to the first input of the autopilot, the output of the autopilot is connected to the input of the rocket rudder control device, the output of the rocket rudder control device is connected to the second input of the autopilot, the input of the radio receiver of the radar head ca homing is connected to the output of the transceiver antenna, and the output of the radio receiver of the active radar homing head is connected to the first input of the on-board digital computer, the output of the modulating pulse generator is connected to the input of the radio transmitting device of the active homing head, the output of which is connected to the transceiver antenna, characterized in that the installation with a radar of illumination and guidance, a direction finder at the frequency of the active homing head was introduced, an optimal filter and a generator for switching off the radiation, the first output of the direction finder at the frequency of the active homing head is connected to the optimal filter and the generator for switching off the radiation, the first output of the generator for switching off the radiation is connected to the input of the multifunction radar station, the second output of the generator for switching off the radiation is connected to the input of the device illumination of the target, the second output of the direction finder at the frequency of the active homing head is connected to a bus by a bus the next input of the digital computer system, and a radio receiver for receiving telecommand commands at the backlight frequency and a command generator for modulating the modulation parameters are introduced into the anti-aircraft guided missile, the output of the radio receiver for receiving telecommand commands at the backlight frequency connected to the second input of the onboard digital computer, the first output of the onboard computer the machine is connected to the input of the shaper of commands for changing modulation parameters, the output of which is connected to the input of the shaper oduliruyuschih pulses.