RU2689008C1 - Method of preparation of controlled missiles launching and control system of rocket weapon system - Google Patents

Abstract

FIELD: rocket equipment.SUBSTANCE: group of inventions relates to the field of guided missile weapon application and can be used in multichannel complexes having means of detecting, tracking targets and direction finding of missiles. Method involves detecting, capturing and tracking several targets, assigning each target to each missile by specifying a channel interval. After each missile is tied to its target and a command is received to launch the missile, the on-board missile equipment is ready to record repeating code parcels. In each premise, a set of parameters of the corresponding channel interval target, which are used in the control system when transmitting commands to the missile and receiving response signals from it, as well as the target type are generated. Recording is performed until its confirmation from on-board equipment of missile. Then, the recorded set of parameters is read out and compared with the transmitted set. In case of their match, write-reading of parameters is terminated and rocket is launched with further controlled flight. In case of discrepancy of set of parameters recorded in on-board equipment, transmitted write-reading procedure is repeated for preset time. If the set of parameters does not match, the missile is launched without flight control with subsequent self-liquidation.EFFECT: shorter time for checking readiness of missile before launch.2 cl, 1 dwg

Description

At the present time, the readiness of armament complexes for firing is becoming increasingly important, with considerable emphasis being placed on the time for preparing the armament and checking its readiness for opening fire after detecting and tracking targets.

A missile weapon system is known, a multistage armament system and corresponding methods [1] of preparation for firing include several weapon controllers (controllers), several firing blocks connected to launching initiation blocks containing a fuse cap for manually disconnecting the signals in each control device . Each weapon control device is connected to the firing unit via a digital communication channel having its own protocol, selected from the network group (CAN), Ethernet, RS422, RS232, and RS485, and several weapon control devices are connected to each other using a normal communication channel from the main device (controller). The method used to control and prepare a multistage system (p. 17-22) consists of sending control signals to several control devices for firing units with an appropriate address, manually turn off the stages alternately, check their readiness, and then send a signal to fire when they are ready. The main disadvantage of such a system is the difficulty in controlling each stage when carrying out sequential control of firing units with manual stage deactivation, and then connecting them and issuing signals for trigger initialization and firing, which leads to low reliability and large time costs for launching.

Also known anti-tank missile system Mizrak-U [2, 3, 4], in which on the launcher transport UR, prepare for launch and carry out the implementation of the sequence of operations start UR Mizrak-U, for which they switch signals in the implementation of the capture target homing (GOS ), program the autopilot, receive the video signal from the HOS, conduct diagnostic testing of the UR and perform the launch. The rocket has a pin fuse and a cumulative warhead to engage armored targets, the delay of the fuse triggering is set before launch with an accuracy of 10 μs. The operator marks on the monitor a target intended to be captured for tracking, if the target is in the firing zone, he energizes the rocket's electrical circuits, ensures the target’s homing target is captured, waits for a signal that the rocket is ready for launch and produces a launch. The disadvantage of this method of preparation for launch is a large amount of action, which leads to long preparation times for firing and is unacceptable for anti-aircraft complexes, whose main task is to fight air targets, whose speeds are much higher than ground targets and to fight air targets have a small time (units and fractions of seconds) of the missile defense to start.

There is a method of preparing the launch of guided missiles, including detecting, capturing and tracking several targets, linking each target to its own missile by setting the channel interval as close as possible in terms of the combination of features and chosen as a prototype. This method is implemented in an anti-aircraft missile and cannon complex [5], which contains a missile weapon control system with target tracking and direction finding equipment, a digital computing system (CWS) with a channel scheduler and a launch console connected to the rocket. These known method of launch preparation and the anti-aircraft missile-gun complex for its implementation provide high combat effectiveness of defeating air targets.

However, when preparing a complex for combat work, when loading an ammunition load of rockets or before launching them manually in a rocket, a number of parameters are established, according to which the rocket interacts with the control system of the complex when the rocket is in summer. This often leads to errors and the rocket flies uncontrollable, like a ballistic one. Sometimes in the process of battery operation, a number of parameters need to be changed at the direction of the higher command post. In this case, it may turn out that the parameters set manually on the rocket do not correspond to those set in the BM, and in fact this makes the BM not effective, or if they launch missiles, they will fly away as ballistic. In addition, the introduction of a correction to the deviation of the input parameters from the nominal when preparing missiles for launches, performed from the commander’s console, is non-technological and unacceptable because of the possibility of introducing errors. Considering that the ZRPK [5] is multichannel, and at the same time there may be several radars in the summer, then in order to exclude interference and the influence of one rocket on another, it is necessary to introduce its own parameters on each rocket before its descent, ensuring its interaction with the control system of the complex in the process flight, targeting and hitting the target. But in general, there should be as many options in the control system as there are BMs in the battery and how many rockets are launched simultaneously. At the same time, when performing combat operations, an operational need arises for defeating various types of targets, including for ensuring the complex’s self-defense. Moreover, the presence of a radar-optical detection and tracking system in the complex allows detecting various types of targets, and the existing preparation of the SD for launch does not ensure their use for various types of targets.

The task of the invention is to reduce the time to check the readiness of the rocket before launch, due to the automatic installation in the rocket of the main parameters of the rocket when interacting with the control system of the rocket armament complex in the time interval from the moment of its launch (switching on the power supply and onboard equipment) to derailment and increase effectiveness of the weapons system through the use of SD for various types of targets, for example, air and ground.

The solution of the task is achieved by the fact that in the method of preparing the launch of guided missiles, including detecting, capturing and tracking several targets, linking to each missile of their target by setting the channel interval, after linking each target to each missile and receiving a command to launch the missile when the onboard is ready missile instrumentation into it (rocket BA) record repeated code sets, with a set of parameters of the corresponding channel interval target used in the system in each package ee management when sending commands to the rocket and receiving response signals from it, as well as the type of target, the recording is carried out until it is confirmed by the onboard equipment of the rocket, after which the recorded set of parameters is read and compared with the transmitted one and if they match, write-read parameters the rocket is launched and launched, followed by a controlled flight, and in case of a set of parameters recorded in the rocket’s onboard equipment that do not correspond to the transmitted parameters, the write-read procedure is repeated for a specified time In the absence of compliance with the set of parameters, launching a rocket without flight control, followed by self-destruction.

The method of preparing the launch of guided missiles is implemented in the control system of the rocket armament complex containing the target tracking and rocket direction finding equipment, digital computer system (CWS) with the channel interval scheduler and launch control panel connected to the onboard equipment of the rocket; comparison circuit, two delay circuits, circuit I1, OR circuit, two inputs of which are connected separately to the outputs of the comparison circuit, the first output of which is also connected to the first input of circuit I1, W The entrance of which is connected to the contact of the missile launch, and the output of the I1 circuit is connected to the control input of the target tracking equipment and direction finding of the rocket through the second delay circuit, and between the second output of the launch console and the second rocket input performing its launch, the I2 circuit is entered, the second input of which connected to the output of the OR circuit, while the two inputs of the comparison circuit are connected separately to the output of the onboard equipment of the rocket and the output of the parcel forming unit for the rocket, which is simultaneously connected to the boron input through the first delay circuit rocket hardware

The essence of the invention lies in the fact that in fractions of a second from the moment of launching the UR (switching on the electric battery and on-board equipment) before the descent, quickly carry out monitoring of the efficiency of its on-board equipment, enter automatically into the rocket before the descent the main parameters of the interaction of the rocket with the control system of the missile system during combat , and after entering the parameters, launch the target designated for this rocket.

To solve this problem, from the moment each rocket is assigned its purpose, the complex’s computer system forms its code message containing information on the required parameters, which will be used to request and receive responses from the rocket in the summer and transfer control commands. After the launch of the onboard equipment of the rocket, the parcel with the CWS is transmitted to the rocket before receiving the hardware response word, the presence of data in the response parcel and their correctness, after which the rocket is considered to be in good condition and launch. Assessment of the readiness of the rocket for launch is carried out when exchanging up to a predetermined number of parcels, each of which fit within the time period of the designated channel interval of the rocket. In the case of a set of parameters recorded in the on-board equipment of the rocket to the transmitted parameter, the write-read procedure is repeated for a predetermined time and, if the parameter set does not match, the rocket is launched without flight control followed by self-destruction.

Introduction in automatic mode, before the launch of each missile, of its parameters for controlling SD in summer, according to its assigned purpose, allows to increase noise immunity, accuracy by eliminating asynchronous interference and mutual influence of missiles in summer on shooting accuracy while simultaneously targeting several SDs to multiple targets or salvo firing, and the ability to take into account the type of target when firing ensures the effective use of the armament of the complex, depending on the current combat situation.

The introduction of the parcel forming unit and logic elements in the digital system of the complex, which perform the functions of interaction with the onboard equipment of the rocket and the target tracking and direction finding equipment of the rocket, using the remote control enabled to ensure that the rocket is ready for launch in a short time, increase the reliability, accuracy, noise immunity of the weapon system, and also ensure the use of anti-aircraft guided missiles for various types of targets.

The invention is illustrated graphic material, where Fig 1. shows a functional diagram of the method of preparing the launch, launch and guidance of guided missiles and the missile system. In the scheme, the following notation:

1 - target tracking and direction finding equipment;

2 - a digital computing system (CWS) with a channel interval scheduler;

3 - unit of formation of the parcel;

4, 5 - the first "СЗ ₁ ", the second "СЗ ₂ " delay circuit;

6 - the first scheme "And ₁ ";

7 - comparison scheme "FSC"

8 - OR scheme;

9 - the second scheme "And ₂ ";

10 - remote start;

11 - anti-aircraft guided missile with control equipment, rocket presence contact and launch elements.

The equipment for tracking targets and direction finding of rockets, a digital computer system with a channel interval scheduler, a launch console, are made in accordance with [5]. All communications of the central computer with the target tracking and direction finding equipment of the missiles, the launch control panel and the missile equipment are carried out via a digital interface communication line made according to the type [6].

A guided missile with control equipment is made, for example, according to the type [7] and [8]. Signals to the rocket are transmitted through wired cables through the connectors of the container.

New newly introduced are: the unit for the formation of the code parcel (3), the comparison circuit (7), the first and second delay circuits (4 and 5), and the logical elements "OR" (8), "And ₁ " (6), "And ₂ "(9).

The parcel forming unit, the comparison circuit, the delay circuit, the logic elements AND ₁ AND ₂ , OR are built on the basis of digital logic circuits according to the examples given in [9].

If a decision is made to fire an emergency warning device, then a “Start” signal is generated in the start panel, which from the first output of the start console goes to the first input of the automatic relay and from the third output of the start panel via the digital bus main serial interface to the inputs of the DCC and the parcel forming unit. On the “Start” signal, the parcel forming unit forms the command word “RECORD” and a data word containing code information about the parameters that ensure the interaction of the UR with the control system of the complex in summer (for example, time delays, frequencies, type of target, etc.) and sends this information to the first input of the comparison circuit (7) and through the first delay circuit (4) to the input of the onboard equipment of the rocket (11). The first delay circuit provides a delay in issuing the parcel's onboard equipment for a time t1 corresponding to the time the power supply battery and the rocket's onboard equipment have reached the mode.

After issuing code words for recording (the specified number of assigned temporary rocket channel interval) and receiving from the onboard equipment (11) of the rocket a message that the information is received and stored, the parcel forming unit (3) issues the READ command in which the rocket sends response code words (response number of parcels) containing the stored information that arrives at the second input of the comparison circuit (7).

The comparison circuit (7) compares the information that came to the first and second inputs, and generates the appropriate signals of the health or malfunction of the rocket, depending on the state of the information that came from the rocket:

- if the values of the information codes that came to the first and second inputs coincide, the missile considers that the missile is working, generates a firing resolution signal (PC), and the “RECORDING-READING” procedure stops;

- if the values and non-zero or zero values of the codes received at the second input do not coincide with the codes at the first input, the “RECORDING” - “READING” procedure is repeated and if during the specified number of time slots after the start of the exchange the word values did not coincide, then he considers that the rocket is faulty and generates a signal to prohibit the firing of an unguided rocket (“NRS”).

Always at the output of the comparison circuit after the “Launch” signal is issued to the missile, the state of the signals “RS” = 1, “NRS” = 0 or “NRS” = 1, “RS” = 0 or before the launch of the RS missile = 0, “ NRS ”= 0.

The logic circuit "And ₁ " (6) is connected by the first input to the first output of the comparison circuit with which the signal "RS" is received, the second input of the logic circuit "And ₁ " is connected to the contact of the missile launch (11), from which the signal "Departure" with the launch of the rocket from the launch. The output of the logic circuit "And ₁ " through the second delay circuit (4) is connected to the input of the target tracking and direction finding equipment, which transfers control commands and captures the missile to control it in summer. The second delay circuit (5) provides a delay in the generation of the Capture command for the rocket direction finding equipment for the time the rocket moves in the container, which eliminates interference at the input of the direction finder before receiving the response signal from the rocket.

In the absence of at least one of the signals “EXCURSION” or “RS” the command premise is not formed and the rocket is not captured by the direction finder.

The signals "RS" and "LDCs" from the output of the comparison circuit (7) are fed to the first and second inputs of the logical circuit "OR" (8). If the complex is ready for combat operation, after issuing the “Start” command from the start panel and completing the exchange of parcels from the output of the comparison circuit, the OR status information is present at the input of the OR circuit: OK “RS” = 1, “LDC” = 0 or faulty "RS" = 0, "LDC" = 1. The signal from the output of the OR circuit (8) is fed to the second input of the circuit “AND ₂ ” (9), the first input of which is connected to the second output of the start console (10), and the output of the circuit “I ₂ ” is connected to the second starting circuit of the rocket ( 11) launching the engine and launching the rocket. The introduction of the “OR” and “And ₂ ” logic circuits ensured the launch and descent of the UR, independently whether it is in good condition or faulty, thereby making it possible to exclude from the ammunition the defective URs. And in the case of the launch of a malfunctioning (unguided) rocket, the “RS” = 0 signal is not generated; a command parcel is not formed and the rocket is not captured by the direction finder. The rocket flies like a ballistic one, and in the absence of control commands, it will self-destruct.

The equipment of the complex detects and takes on target tracking, identifies them by type, determines their characteristics and motion parameters, and sends them to the central computer system via a communication channel. The Center estimates the targets according to the degree of danger, determines the sequence of their shelling, and with the help of the time slot scheduler assigns each missile its own target, interconnecting them. After the missile has been linked to its target, from the central computer system, via the interface output to the launch console (10), a signal is issued to allow the launch of the electric battery and the activation of the rocket hardware. This signal from the first output of the start-up panel receives a “Start-up” signal at the first input of the rocket, the power supply and on-board equipment turn on and go into the rocket mode. At the same time, the CWC in the block for forming a parcel to a rocket forms a code parcel that takes into account the binding of its target to each rocket by specifying a channel interval. The package contains the command word “RECORD” and a data word containing code information about the parameters that ensure the interaction of the rocket in the summer with the control system of the missile complex, and the information on the required parameters to be used to request and receive responses from the rocket in the summer and the transfer of control commands, and the type of goal. From the output of the code parser, the information is fed to the first input of the comparison circuit and through the first delay circuit SZ ₁ to the onboard equipment of the rocket. The on-board equipment of the rocket, after receiving the parcel, decodes it, remembers, sets the specified parameters and informs the CWS that the information is received and recorded. From the output of the parcel forming unit through SZ ₁ , the READ command enters the onboard equipment of the rocket; on this command, the onboard equipment generates a response parcel with a message about the set parameters. This information from the onboard equipment of the rocket goes to the second input of the comparison circuit. The comparison circuit compares the parcels sent from the parcel forming unit and that received from the onboard equipment of the rocket, and if they coincide, a firing resolution signal “RS” = 1 is produced, which through the OR circuit goes to the second input of the “And ₂ ” circuit, to the first the input of which receives a signal from the second output of the launch console, and the output of the “I ₂ ” circuit produces a “Start” signal. From the output of the “I ₂ ” circuit, the “Start” signal arrives at the second inlet of the rocket, setting fire to the engine igniter and the rocket begins to move in the container before exiting the container. From the moment the rocket starts to move, the contact (jumper) of the rocket’s presence is broken, and the “Retract” signal appears, which goes to the second input of the “I!” Circuit, at the first input of which the RS-31 rocket has a good signal from In the “I ₁ ” scheme, a “RK” signal is generated, which arrives at the input of the target tracking equipment and missile direction finding to form control commands and capture the missile by the direction finder and form the code command package for the missile guidance control.

The command parcel sent to the rocket contains information in the parameters that were installed on the rocket before the launch, which allowed recognition and decoding of rocket code in the summer of the code intended only for it, extracting commands from the code parcel to control the rocket when aiming at the target, and to provide in the summer at the same time several rockets having other channel intervals in which their parameters were established for each SD. This eliminated the appearance of interference in the summer and provided high noise immunity and accuracy of missile guidance when firing several closely spaced targets, including salvo firing. At the same time, when deciphering a code parcel on a rocket in summer, the type of the target for which the SD is induced is determined, which ensures its effective use for hitting the target.

The set of technical solutions allowed to ensure that the missile is ready for launch in a short time during the period from launch to missile launch, enter the necessary parameters for the interaction of the missile in summer with the control system of the missile complex, which improved the reliability, accuracy, noise immunity of the control system while simultaneously targeting several missiles, effective firing of several targets, including during salvo firing and optimal use of the rocket for firing various types of targets.

Sources used

1. A missile system, a multi-stage weapons system and related methods. U.S. Patent No. 09127918 dated 09.09.2015, F42B 15/12, F42B 15/01, F02K 9/95.

2. Jane's Air-Launched Weapons, 2009, pp. 155, 611, 612.

3. Forecast International / DMS Missile. Turkish ATGWs, September 2014.

4. IHS Jane's Weapons: Air-Launched, 2010-2011, pp. 140, 141.

5. ZRPK according to the patent of the Russian Federation No. 2381818, dated 10.04.2008, F41H 11/02, F41G 7/20, F41A 23/42.

6. Mainline serial interface system of electronic modules, GOST R52070-2003.

7. Guided projectile according to the patent of the Russian Federation No. 2 442 516 of 09/07/2010, F42B 12/56.

8. Radio-controlled anti-aircraft missile according to the patent of Russian Federation №2373486 of 06/02/2008 F42B 15/00.

9. "Analog and integrated circuits". Reference manual edited by Yakubovsky "Radio and communication", 1990 p. 46-58.

Claims (2)

1. The method of preparing the launch of guided missiles, including detecting, capturing and tracking several targets, linking to each missile of its target by specifying a channel interval, characterized in that after binding to each missile of its target and the receipt of a command to launch the missile when the onboard equipment of the missile is ready it is used to record duplicate code messages, and in each package they form a set of parameters of the corresponding channel interval target used in the control system when transmitting commands to the response and receiving the response signals from it, as well as the type of the target, are recorded until it is confirmed by the onboard equipment of the rocket, after which the recorded set of parameters is read and compared with the transmitted one, and if they match, the reading and reading of parameters is stopped and the rocket is launched subsequent controlled flight, and in the case of a set of parameters recorded in the onboard equipment of the rocket, the transmitted write-read procedure is repeated for a specified time and, if there is no match, the set and the parameters carry out the launch of a rocket without flight control with subsequent self-destruction. 2. The control system of the rocket armament complex containing the target tracking and rocket direction finding equipment, digital computing system - centralized control system with channel interval scheduler and launch control panel connected to the onboard equipment of the rocket, a parcel formation unit for the rocket is introduced, comparison circuit , two delay circuits, “I1” circuit, “OR” circuit, two inputs of which are connected separately to the outputs of the comparison circuit, the first output of which is also connected to the first input of the “I1” circuit, the second input of which is with the contact of the missile launch, and the output of the “I1” circuit through the second delay circuit is connected to the control input of the target tracking and direction finding equipment, and between the second output of the launch console and the second input of the rocket for launching it, the “I2” circuit is entered connected to the output of the OR circuit, while the two inputs of the comparison circuit are connected separately to the output of the onboard equipment of the rocket and the output of the parcel forming unit for the rocket, which is simultaneously connected via the first delay circuit to the input of the onboard equipment missiles.

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