RU22991U1 - SYSTEM FOR AUTOMATED START-UP FROM THE CARRIER OF THE MOBILE ROCKET OF THE PORTABLE ANTI-AIR MANAGEMENT SYSTEM OF THE TYPE "Igla" - Google Patents

Abstract

1. System for the automated launch from a carrier rockets of a portable anti-aircraft missile system (MANPADS) of the Igla type, containing launch modules (PM), each of which includes a hollow power beam with load-bearing supports, centering elements for mounting on a carrier and with clamps for fixing on the sides of the beam of launch tubes with missiles from the MANPADS, missile unlocking mechanisms, protective front covers with mechanisms for opening them, while each PM has a gas supply line through the inlet fitting of compressed gas to the optical homing head (OGS) missiles and electro-pneumatic valves (EPC), means for connecting missiles to the PM, a remote control (PDU) with a communication unit, as well as the PM control electronics located in the cavity of the beam, characterized in that an electronic control module and communications (MUiS), connected to the remote control and electrically connected to each PM, while all PM are equipped with receiving devices for docking ground-based blocks of electro-gas power supply (NBP), the mechanisms of rassoporeniya rockets and the opening of the protective covers are made in the form of mon of e-actuators, gas lines are connected through check valves to receiving devices, each inlet fitting is equipped with a locking mechanism and is connected to the gas line through a rocket selection EPA, to the output of which a pneumatic actuator for opening the protective cover is connected and through an additional EPK a pneumatic actuator for uncoupling this rocket. 2. The system according to claim 1, characterized in that the MUIS contains a communication unit with a PM, a communication unit with a remote control, a PM selection and PM control unit, a command formation unit for the simultaneous descent of two missiles in salvo mode

Description

NS .., „(11111 Illll lilt III

System for automated launch of Igla-type portable anti-aircraft missile system from the carrier rockets

The proposal relates to ground, air or surface-based launchers and can be used to launch missiles in launch tubes from a Igla-type portable anti-aircraft missile system (MANPADS).

Known twin installation for launching anti-aircraft missiles for personal use, containing a base with a clip, a rotary part with a seat, a swinging part with fastening elements for the launch tubes, gears for shifting the handle of the drive for controlling the launch of each rocket and a launch selector made in the form of a handle with a trigger lever and a mode translator firing and a dispenser kinematically connected with the trigger lever and with the mechanism for transferring the handle of the launch control drive of each rocket, see RF patent N 2088877, you anny by application 95119765, IPC 6F41A23 / 34, F41F3 / 04.

The installation can be mounted on a base with sliding beds when firing from the ground or on a vehicle equipped with the same type of mount. The installation ensures the placement of two missiles in launch tubes and their simultaneous or sequential launch directly by the operator, as well as during

the need arose to use them without any changes to launch from the operator’s shoulder. Not for use with an air vehicle.

MPKR41RZ / 04

one of which includes two missiles with thermal homing heads and a common cooling system for photodetectors. The fairing of each homing head is protected by a mechanically opening petal lid. The complex also includes launch controls and a control system with an interface unit that enables the interaction of missiles and helicopter weapon systems, see V.Viktorov, French Mistral air defense systems, Foreign Military Review, 1987, N4, Aviation Week, 1985, v. 122, N2 , from. 70; Prospect of the air-to-air complex Mistral of MATRA DEFENSE; NTI, N7-8.1996, p. 46-49.

The closest analogue (prototype) is an air-based launch module (PM) according to US patent 4,429,611, IPC F41F 3/04. The PM is designed to launch the Stinger MANPADS missiles from the aircraft and includes a central supporting frame with attachments to the aircraft, lodgement attachment points for launch tubes with quick release tools and a guide for quick installation of launch tubes with missiles in the desired position and mounts using connection tools with a power supply system and a cooler feed system to the launch tube.

The PM frame consists of an elongated central U-shaped channel, in the cavity of which a cylinder with a cooler (compressed gas), a power source, a control device and other elements are placed.

Launcher tubes with missiles are located on either side of

the central channel and are located in two pillars equipped with locks (clamps) - front and rear. Every front lock

consists of a fixed lodgement and a movable element, which is held in position by the thumbscrews. The movable elements are adjacent to the fixed tool holders and

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open outward in such a way that access to the launch tubes is provided from the sides.

The back support has a similar design. The movable cover elements rotate relative to the axes in the fixed tool holders and are held in place by wing screws. The ability to rotate the covers allows you to remove the launch tube from the PM movement down and to the side. This allows you to equip the PM standing from the side, avoiding situations when the equipment operator is in front or behind the launch tube with a rocket.

The guide for the launch tube includes lodgements with floating contact groups mounted on spring-loaded plungers. The pins of the contact group are connected to the flat holes in the brackets for the corresponding launch pipe. These brackets are provided by the standard design of launch tubes for connecting the trigger mechanism when the operator starts the launch from the shoulder. The guides are used to align the pipe in the axial direction and give it a position in the axial direction relative to the housing, in which you can put the pipe in a fixed position by turning it up and at the same time connect it to the gas supply socket in the system and to the connectors of the electronic control system.

A lock is provided on each tube of the rocket, which includes a gripper, which is mounted on an axis in the bracket and is equipped with a lever for opening the lock. Lock hooks mesh with standard brackets on the front of the launch tubes.

The PM contains electronics controls and triggering means for launching the corresponding rocket through cable communication with the operator console in the aircraft cabin

apparatus, which allows the pilot or operator to launch a rocket of his choice. When adapting the system to use other types of missiles, the control unit is refined by inserting other boards in a known manner.

The homing thermal heads cooling system includes a cylinder with cooling gas. The gas supply socket connects the gas cylinder to the system, which includes a line for distributing gas through two separate lines and connecting via electrically controlled valves to the corresponding pipe. The PM electronic control system is located in the central channel and includes a power supply unit connected to the control unit, as well as circuits necessary to activate and control the operation of the homing head and missile guidance system. A description of the electronic system is not provided. The safety block is included in the switching unit, which excludes start-up until the PM is fully equipped and ready for cocking. When cocking, the PM check is removed from the starting module.

Each of the launch tubes at both ends is covered with protective caps, which are automatically reset when the rocket is launched (due to which actions are not explained).

The mentioned PM, intended for consecutive launches of missiles of this type from air carriers (Stinger), cannot be used for launching widely used missiles from Igla type MANPADS due to structural differences, and does not provide the possibility of multiple launch rockets simultaneously, which is often necessary due to the insufficient effectiveness of the impact of one relatively low-power warhead on a modern highly protected target. All rocket launch control, in fact, is carried out manually by the operator.

The technical result of the proposal is the ability to launch missiles from the Igla type MANPADS (including using standard ground-based MANPADS power units) both in single-shot mode and in multiple rocket launcher mode with two missiles simultaneously simplifying the operator’s work by transferring individual operations missile launch control equipment. The main mode of operation is volley shooting. The proposed system makes it possible to fire missiles of the Igla family (including all known modifications) from various types of carriers: helicopter, infantry fighting vehicles, armored personnel carriers, boats, with minimal modifications to the system associated with the conditions for its specific placement on the carrier, and also allows the use of regular infantry infantry fighting vehicles complex.

This is achieved by the fact that in a system for launching MANPADS containing PM, each of which includes a hollow power beam with load-bearing supports, centering elements for mounting on a carrier and with clamps for securing launch tubes with missiles from the MANPADS on the sides of the beam, missile deployment mechanisms , protective front covers with mechanisms for opening them, while each PM has a gas supply line through the inlet fitting of compressed gas to the optical homing head (OGS) of the rocket, means for connecting the rockets to the PM, remote control On-board control (RC), as well as PM control electronics located in the cavity of the beam, an electronic control and communication module (MUiS) is introduced, connected to the remote control and electrically connected to each PM, while all PMs are equipped with receiving devices similar to receiving devices for grounding of electric gas supply units (NBP), mechanisms of missile deployment and rotation of protective covers are made in the form of pneumatic drives, gas lines are connected through return

valves to the receiving devices, each inlet fitting is equipped with a locking mechanism and is connected to the gas line through an electro-pneumatic valve (EPC) for selecting a rocket, to the output of which a pneumatic actuator for opening the protective cover is connected and through an additional EPC - an opening mechanism for this rocket. MUIS contains a communication unit with a PM, a communication unit with a remote control, a PM selection block for operating and controlling a PM, a volley forming unit, a request for a remote control for activating the next air defense missile and missiles, and a message forming unit on the remote for the status of the PM, missiles and the entire system . If there is an angular velocity meter on the carrier, the MUIS can include an angular velocity analysis unit to increase noise immunity during automatic target capture and during volley fire. The PM control electronics includes a PM control unit, a target capture and missile launch control unit, an NBP selection and activation unit, including spring cocking mechanisms and electromagnetic trigger mechanisms for opening the NBP sealing membranes located in receiving devices for installing the NBP, and the control of the EPA of protective air drives covers, EPA pneumatic drive of the missile deployment mechanism, missile launch delay block, position sensors of protective covers and stoppers, sensors for the presence of NBP and their activation. The position sensors of the protective covers and the position sensors of the rocket stoppers contain serially connected switching elements of the ignition circuit of the starting engine. Each PM is equipped with a removable horseshoe-shaped check blocking unauthorized start-up, which is made in the form of a horseshoe-shaped staple that prevents the protective covers of the PM from opening if there is one. Devices for electrical docking of missiles, made in the form of a guide spring-loaded casing with a centering hole. The bearing supports of each PM have a bottom

and from above the centering elements for precise installation on the carrier of several PM with the possibility of placing them one below the other (whatnot, bunch), as well as in rows. When placed on various media, if necessary, changes are made to the MUiS communication unit with the remote control to ensure adaptation.

The essence of the proposal is illustrated by drawings and diagrams.

Figure 1 shows a block diagram of a system for the automated launch of missiles such as Needle.

Figure 2 shows a General view of the PM.

In Fig. 3 shows a functional diagram of the PM, in Fig. 4 is a General view of the device for connecting the launch tubes from MANPADS with missiles, in Fig. 6 is a General view of the mechanism of missile deployment and a General view of the inlet fitting, Fig.7 is a General view of the protective front covers and checks.

The proposed system (see figure 1) for the automated launch of missiles from MANPADS type Igla includes from one to several PM 1 (preferably at least two). Figure 1 shows an example of a system containing four modules, two on the left and right side of the carrier. The start-up modules are electrically connected to MUiS 2. For bus communication with the MUiS, bus architecture is used. PM addressing, depending on their position on the carrier, is done by jumpers on the cable connectors.

MUiS is electrically connected to the remote control 3, from which the operator controls the launch of missiles. The specific design of the remote control depends on the type of media and the equipment available on it and, at a minimum, contains a power supply unit (PSU) 4 (27 V), with bodies for turning it on, button 5 () to activate the NBP, button 6 (Start) to issue Command Permission to launch missiles. It is preferable to use buttons for these control commands, since

Using them, short-term commands are issued. A longer command will be from the button 6 Permission to launch missiles.

In a preferred embodiment, the remote control 3 should have a display unit 7 (Bindik) to monitor the operation of the system. The multifunctional weapon control display on the carrier can serve as this unit, or it can be sound and light indicators receiving information from MUiS 2 and controls. The remote control 3 has a communication unit 8 () for connection to the M&S 2. Through this two-way communication block (preferably in the form of a serial asynchronous communication line), the M&S and the remote control exchange information signals in a known manner. The remote control may include a block of additional commands and control messages 9, connected to the communication unit 8, for example, for monitoring the system for automatically starting and transmitting information about target parameters to media devices from the media device. MUIS contains:

two-way communication unit 10 (and BforSobsche on the remote control) with the remote control, which includes a block for generating messages on the remote control;

two-way communication unit 11 () with PM;

block 12 (Bivy PMP and Management) PM selection and PM management;

block 13 (BformirovZalpa) team formation for the simultaneous descent of two missiles in salvo mode;

block 14 (BZaprosNBP) the formation of a request for remote control for the launch of a rocket and (or) NBP, as well as

a block of filters and stabilizers 15 (BF filters and Stabilizers), which is connected to the power supply unit 4 of the remote control at the input and with PM 1 at the output,

To work with carriers that have blocks giving information about the parameters of the target’s movement, range to the target and its angular velocity, for example, radar, MUiS contains block 16 (BANalizUglSkor) analysis of the magnitude of the angular velocity coming from PM 1 and from the media through the remote control from block 9 .

Blocks 6,10,11,12,13,16 are made on microcontrollers of the 1830BE51 type. Examples of the implementation of various units using microcontrollers are given, for example, in the book of V.V. Stashin, A.V. Urusov Designing digital devices on single-chip microcontrollers, Moscow, Energoavtoizdat, 1990. Asynchronous serial communication lines are made using standard transceiver microcircuits using the RS-422 protocol.

MUiS communication with remote control and PM is carried out by electric cables (not shown). PM has a connector 17 (figure 2) for connecting a cable from MUiS. The launch module has a hollow power beam 18, with load-bearing supports 19, centering elements 20 for mounting on the carrier and with clamps 21 for quick fastening on the sides of the rocket beam in the launch tubes 22 of Fig. 3.6 (not included in the PM) of the MANPADS . The PM is equipped with mechanisms for unlocking the rockets 23 (stopper), protective front covers 24 with mechanisms for opening them in the form of pneumatic actuators 25 (caps), while each PM has a gas supply line 26 through the inlet fitting 27 of compressed gas to the optical homing head (OGS) of the rocket from electropneumatic valves (EPC) 28 and is equipped with means for electrical connection of 29 launch tubes with missiles to the PM. In the sealed cavity of the power beam 18, the PM control electronics is located. Bearing supports 19 have fastening and centering elements 20 and above and below, allowing

mount PM both on the carrier and between each other (one above the other), in the form of whatnot and (or) bunch. Clamps 21 for quick fastening along the stoppers of the beam 18 of the launch tubes 22 with missiles are located on the front and rear supporting supports 19. The mechanisms 25 for opening the front protective covers 24 are mounted on the front end of the power beam 18. The PM is equipped with a receiving device 30 (Fig. 4) for connection full-time TNBP 31 (Fig.Z, shown conditionally). The receiving device 30 is located at the rear end of the power beam 18. The PM contains check valves 32 connected to the receiving devices 30 and EPK 28 rocket selection. To the EPK 28 rocket selection is connected to the nozzle 27 for supplying cooling gas to the OGS of the rocket, the pneumatic actuator 25 for opening the protective covers 24 and the EPA 33 for connecting the pneumatic actuator 23 of the rocket release mechanism. The PM control electronics contains a control unit 34 (BUG controlStart and Rocket Launch), target acquisition and missile launch, block 35 (BZaderStartRocket) missile launch delay, block

36 (BO selection and actions NBP UprElPnevKlap) selection and

the activation of the NPL and the control of the EPA, the PM control unit 37 (BUpravl PM), connected through the block 38 () of communication with two-way communication with the MUiS 2 and two-way communication with the block 34 control capture of the target and missile launch, block 36 selection and activation of the NBP and EPA control. The start-up module is equipped with position sensors 39 of the protective covers and sensors of the position of the stoppers 40. The block 36 for selecting and activating the NBP and EPK control is connected to the EPK 28 for selecting the rocket and EPK 33 for connecting the pneumatic actuators for opening the rockets to control their activation and inclusion. To determine the presence of NBP in the PM, sensors 41 of the presence of idle NBP were introduced. Block 35 delay the launch of the rocket is connected to the control unit capture the target and the launch of the rocket 34 and through the communication unit 38 with MUiS.

The control unit for capturing the target and launching the rocket 34 is connected with means for connecting 29 missiles in the launch tubes to the PM and has means for detecting the presence of a rocket on the PM, for example, in the form of a closed circuit through a rocket that opens when the rocket leaves the PM. The PM has a power supply unit 42 containing voltage stabilizers, the input of which is connected to the MUiS 2. The unit 38 for communication of the PM with MUiS contains means for two-way communication using the RS-422 protocol, which is performed using standard microcircuits.

Blocks 34,35,37,38 are made on microcontrollers type 1830BE51.

In the current embodiment, the four receiving devices 30 shown in Fig. 4 are structurally made in a single unit fixed to the rear end of the power beam 18. Each receiving device is equipped with a spring shock cocking mechanism 43 and an electromagnetic trigger mechanism (not shown). Each receiving device is made in the form of a socket to which a gas line is connected, and an electrical connector for connecting power circuits and controlling the NBP. In addition, the socket is equipped with a latch for securing the NBP fitting against loss. It is envisaged to connect one cylinder of a larger capacity to the gas main for multiple launch of missiles. The sensors 39 of the protective front covers and sensors 40 of the missile deployment mechanisms installed in the PM are mechanically connected to the pneumatic actuators of the corresponding nodes, while the sensor configuration elements sequentially connect the ignition target of the launch engine of the corresponding rocket and provide information about their position to the PM control unit 37.

unauthorized opening of the protective front covers and, therefore, blocking the connection of the rocket launch engine. The check is removed during combat work after equipping the PM with launch tubes with missiles.

Means for connecting MANPAD launcher tubes to PM 29 are located on the middle support support 19 PM to the right and left, (see figure 5). Each device is made in the form of a guide box casing 45 with a centering hole 46 and an electrical connector 47. The box casing is equipped with spring elements. Electrical connector, provides electrical communication of control electronics through the launch tube with the rocket. The box casing provides two functions for PM equipment - a guiding element for the seat of the MANPADS launch tube and a protective element for the contacts of the electrical connector. Each bearing support 19 is provided with centering elements 20 (a pin above, a hole below) and openings 48 for connection with a carrier or with another PM.

When installing a launch tube with a rocket, its pin sinks into the centering hole of the box casing, which ensures the articulation of the electrical connector elements and the connection of the rocket's electrical circuits to the control electronics.

On the front support 19, gas supply fittings 27 (see Fig. 6), equipped with spring-loaded fixing mechanisms 49, are located on the right and left.

The control unit 34 for capturing the target and launching the rocket was borrowed from MANPADS Igla (Igla portable anti-aircraft missile system (9K38), (Moscow, Military Publishing House, 1987, p. 50) and is designed to prepare the rocket for launch, to capture the target and apply voltage to missile launch chains: This block carries out the spinning of the gyroscope rotor of the OGS gyrocoordinator, automatic locking and snapping, processing and

evaluation of signals from a rocket when a target is captured by a rocket. When salvo firing, information about the capture process through blocks 37 and 38 enters MUiS 2, which, through the volley formation block 13, firstly, delays the start of the missile launch program, and secondly, after the start of launch, synchronizes the launch processes for simultaneous missile departure different PM during salvo firing. Through the block 36 of the selection and activation of the NPL and the control of the EPA, the block 37 controls the EPA of the drive of the stopper of the rocket and connects the circuit of the starting engine to the block 34 of the control of target acquisition and missile launch. From MUiS 2 through block 38 commands are issued to enable start and start blocking.

The operation of the system for the automated launch of MANPADS missiles from the carrier includes the following steps:

-installation of the system on the media;

-fitting the system with missiles in launch tubes from MANPADS and PM NBP equipment from MANPADS;

- turn on the system (standby mode);

-fighting work.

Basically, as a remote control 3, the display control means already available on the medium are used. MUiS 2 is connected to the remote control via a cable, and PM fixed to the carrier is attached to it. PMs are attached to the carrier with their fastening elements 48, which are available on the supports, while the exact spatial fixation is provided by the centering elements of the supports 20. Electrical connection of each PM and MUiS is carried out through the PM connector 17. To equip the PM, a rocket in the tube from the MANPADS type Igla is stacked, being on its side, which eliminates the danger to the equipment. A pipe with a rocket is laid on the lower parts of the clamps on the front and rear supports, ensuring that the pin of the launch tube penetrates into the centering hole 46 of the guide casing

45. Successively lower the clamps on the front and rear supports and fasten the locks, insert the inlet fitting 27 into the hole of the launch tube of the rocket and fix it using a spring mechanism 49 with a bayonet connection. To equip the PM NBP, the NBP nozzle is inserted into the socket of the receiving device 30, after which the shock mechanism 43 of the NBP cocking is cocked. The delivery package for MANPADS, in one package, includes two missiles in launch tubes and four NBPs. Separately supplied NBPs for reusable use.

The front protective covers 24 PM close the front end of the rocket tube, ensuring its dust and dust protection during transportation on the carrier. The horseshoe-shaped check 44 prevents the opening of the protective front covers and, therefore, prevents the switching of the starting engine circuits, ensuring the safety of all work on equipment - unloading. The check is removed after the equipment. Unloading PM is carried out in the reverse order.

The system is turned on before combat work or with the start of combat work, so we will not separate the stage of turning on the system separately, considering it as a stage of combat work.

At the beginning of combat work (duty), from the remote control 3 from the power source 4, power is supplied to the MUiS 2 and after filtering in block 15 is fed to other blocks of MUiS 2 and PM. Through secondary power supplies PM 42, power is supplied to the PM units. Block 12 MUIS, through block 11 communication MUIS with PM sequentially, periodically polls PM on an asynchronous communication line. At this time, the unit 37 PM collects information about the available resources of the PM and their state of the PM, using the state of the sensors 39,40,41 and signals from block 34. Upon receipt of a request via the communication line, this information is transmitted from block 37 through block 38 to MUiS 2 . It

the message, for example, contains information about the presence of missiles and launch tubes at each PM site, the number of unused NBPs, the position of the protective covers and stoppers.

Based on the information received, the PM selection and PM control unit 12 issues a command to the NBP request block 14. The NBP request block issues a message to the remote control 3 about the system’s readiness to start combat work and checks whether the response with the remote control meets the established standards, for example, that this is a one-time response command that should come after the request and have a given duration, This is necessary to increase reliability and exclude the execution of the command to start the NBP from interference. The request can be displayed on the display unit 7 on the remote control and processed by the operator by briefly pressing the button 5 to enable the launch of the NPC. In an automated media control system, this command can also be generated automatically when the target enters the launch zone and the commander has permission. The command from the start enable button 6 is issued after combining the aiming axis of the PM with the direction to the selected target after it enters the launch zone. Upon receipt of the command to start the NBP from the remote control unit 12 randomly selects PM, from among those who have the resource to work and issues a command to the selected PM to start work. PM received a command in the control unit 37 PM from the communication unit 38, issues a command to block 36 selection and activation of the NBP and EPA control. Block 36 randomly selects a missile and an NPL from those available on the PM and activates the selected NPL and connects to it a block 34 for controlling target acquisition and missile launch, as well as a missile selected for operation, while simultaneously connecting the corresponding rocket selection EPK 28. The supply of power to the electromagnet of the trigger mechanism of the receiving device 30 NBP triggers the trigger mechanism, which produces the opening of the NBP,

in this case, the NBP produces high pressure gas and power supplied to the rocket. Through EPK 28, high-pressure gas enters the pneumatic actuator 25 of the front protective cover 24, which at the same time opens and holds in this position during the entire duration of the combat operation. Through the inlet fitting 27, high-pressure gas enters the rocket to cool the OGS. The PM control unit 37 controls the output of the NBP mode by voltage and by the response of the sensor 39 of the front protective cover by gas pressure and in the absence of one of these events, it can give a command to choose another NBP for operation.

Block 34 control capture of the target and the launch of the rocket promotes the rotation of the gyroscope rotor of the coordinator of the OGS, processes and evaluates the signals received from the rocket when the target is captured from the OGS and if the command permits the start from the button 6, or the command replacing it from the block 9 of the remote control, automatically disarms the gyro coordinator OGS and issues to the PM control unit 37 a message about the readiness of the missile to start the launch program (charging the onboard power supply of the rocket in flight mode, charging the warhead, removing the cancer s from the stopper, power-on booster rockets).

This message is received from each operating PM on the M&S through blocks 37, 38, 11. Volley formation block 13 taking into account control commands from the remote control (through block 12), the time elapsed from the start of target acquisition by the first missile, and, for example, target parameters coming from block 9 remote control through block 12 delays the start of the missile launch program (through block 35 delay the launch of the missile PM) the first to capture the target until the target is captured by the second missile or the end of the specified waiting time. For simultaneous launch of missiles, this is necessary, for example, to prevent smoke from blocking the engine of one missile line of sight on the target of another

missiles, the command to remove the delay start is received simultaneously on all missiles. Block 35 delay the launch of the rocket removes the delay if the rocket is ready for the start of the launch and prohibits the launch of the rocket in this cycle of work, if at the time of obtaining permission from the block 13 MUIS missile is not ready to start. The launch of this rocket will be possible only after releasing the button 6 of the remote control and its secondary. pressing and repeating the OGS target acquisition cycle.

To increase safety, the ignition circuit of the starting engine is connected to the control unit 34 for capturing the target and launching the rocket only after opening the protective covers and removing the rocket from the stopper by introducing into the sensors 39 and 40 the corresponding switching circuits. After the launch of the rocket, the EPK control unit 36 holds the EPK valve 33 of the pneumatic actuator of the rocket deployment mechanism for some time open, so that the gas remaining in the pneumatic actuator expires into the atmosphere through the tube cut off at the launch of the rocket (this is accessory accessory). The power supply from the rocket selection EPK 28 is removed immediately after the rocket launch, while the gas path is closed and the high pressure gas remaining in the NBP can be used as an additional source when launching the second rocket. The protective front covers and levers of the pneumatic drives of the opening mechanisms are returned to their original position under the action of return springs contained in them.

The angular velocity analysis unit 16 receives with the PM the magnitude of the angular velocity of the line of sight, measured by the OGS. As you know, this operation relates to the main functions of the OGS on missiles with homing on the target, which include MANPADS missiles of the type "Needle. The value of the angular velocity of the target, as a rule, is also measured by the means of the medium. Block 16 compares these angular velocities with each other and issues a block 12 with a message about the starting modules

angular velocity exceeds a predetermined threshold. Block 12 select PM and control through block 11 to a specific module command to repeat the cycle of target acquisition. This command is transmitted via an asynchronous communication line to the PM communication unit 38 with the M&S and to the PM control unit 37. The latter instructs the block 34 control capture of the target and the launch of the rocket to repeat the capture cycle. Block 34 arrests the OGS gyrocoordinator. In this case, the optical axis of the coordinator is combined with the sighting line PM. After that, the target is captured by the system.

As follows from a review of the operation of the system, it is equipped with all means for installing on a carrier and firing MANPADS from the Igla complex. At the same time, to launch missiles, it is enough to supply power to the system, combine the PM sighting line with the direction to the target located in the launch zone, hold this direction and issue commands that allow the launch of the NBP and the launch of the rocket. The rest of the pre-launch and launch operations, the system for the automated launch of missiles will perform automatically.

The proposed technical solution formed the basis for the development and manufacture of several samples of a system for the automated launch of Igla MANPADS missiles. Currently, one of the prototypes has successfully launched missiles of the “Needle on target.

USEFUL MODEL FORMULA

System for automated launch of Igla-type portable anti-aircraft missile system from the carrier rockets

1. A system for the automated launch from a missile carrier of a portable anti-aircraft missile system (MANPADS) of the Igla type, containing launch modules (PM), each of which includes a hollow power beam with load-bearing supports, centering elements for mounting on the carrier and with clamps for fixing on the sides beams of launch tubes with missiles from the MANPADS, missile unlocking mechanisms, protective front covers with mechanisms for opening them, and each PM has a gas supply line through an inlet fitting for compressed gas to the optical the homing head (OGS) missiles and electro-pneumatic valves (EPC), means for connecting missiles to the PM, a remote control (RC) with a communication unit, as well as the PM control electronics located in the cavity of the beam, characterized in that an electronic control module is inserted into it and communications (MUiS), connected to the remote control and electrically connected to each PM, while all PM are equipped with receiving devices for docking ground-based blocks of electro-gas power (NBP), the mechanisms for unlocking missiles and opening protective covers are made in the form of a stump moprivodov, gas lines are connected through check valves for the receiving devices, each provided with an inlet fitting and locking mechanism connected to the gas manifold through EPA missile selection, which are connected to the outlet opening pneumatic

protective cover and through an additional EPA pneumatic drive of the deployment of this rocket.

2. The system according to claim 1, characterized in that the MuiS contains a communication unit with a PM, a communication unit with a remote control, a PM selection and PM control unit, a command formation unit for the simultaneous descent of two missiles in salvo firing mode, a remote control request generation unit for the activation of the next NBP and missiles and the unit for generating a message on the remote control about the state of the PM and missiles, and the unit for selecting the PM and the PM control, the unit for forming the team for the simultaneous descent of two missiles in salvo firing mode, the unit for generating the request for the remote control for launching the next NBP and the missiles two-way communication with the remote control and launcher modules through the corresponding communication blocks and the remote control message generation unit, and the command formation unit for the simultaneous descent of two missiles in salvo firing mode, the remote control request generation unit for activating the next NPL and missiles are additionally connected to the PM selection unit and PM management.

C. The system according to claim 1, characterized in that the bearing supports of each PM have bottom and top centering elements for precise installation on the media of several PM with their location one under the other (whatnot, bunch), as well as in rows.

4. The system according to claim 1, characterized in that each PM is equipped with devices for the electrical connection of missiles, made in the form of a spring-loaded guide casing with a centering hole.

b. The system according to claim 1, characterized in that the receiving devices for installing the NBP are equipped with spring cocking mechanisms and electromagnetic trigger mechanisms for opening the NBP sealing membranes.

b. The system according to claim 2, characterized in that the PM contains a control unit for capturing a target and launching a missile, a delay unit for launching a missile, a unit for selecting and activating an NSP and EPA control, an MP control unit connected through a communication unit with two-way communication with MUIS and two-way communication with the control unit for capturing the target and launching the rocket, the unit for selecting and activating the NBP and EPA control, and connected to the sensors for the position of the protective covers and sensors for the position of the stoppers; a unit for selecting and activating an NPL and EPA control is connected to an EPC for selecting a missile and an EPC for connecting pneumatic actuators of missile deployment and to sensors for the presence of unused NBP; the missile launch delay unit is connected to the target capture and missile launch control unit and through the communication unit with the MUiS; the control unit for capturing the target and launching the rocket is connected with means for connecting launch tubes with missiles to the MP.

/. The system according to claim 6, characterized in that the position sensors of the protective covers and the position sensors of the stoppers contain sequentially connected switching elements of the ignition circuit of the starting engine of the corresponding rocket.

8. The system according to claim 7, characterized in that each of the PM is equipped with a removable horseshoe-shaped check blocking the unauthorized opening of the protective covers.

9. The system according to claim 2, characterized in that it contains a block for analyzing the angular velocity of the target, measured by means of PM and remote control.

additional EPA - the mechanism of deployment of this rocket. MUIS contains a communication unit with a PM, a communication unit with a remote control, a PM selection block for operating and controlling a PM, a volley forming unit, a request for a remote control for activating the next air defense missile and missiles, and a message forming unit on the remote for the status of the PM, missiles and the entire system .

The proposed system makes it possible to fire missiles of the Igla family from various types of carriers.

8 s.p. f-we, 7 ill.

Z. PDU

8.

7 Bindic

4 PSU

9.block

optional ix commands and messages

2.MUiS

Y. and Bfor Forces on the remote control

14.BZ Request NBP

12. B Selection of PMP and Management

-tlm.13.BFormirov Volley

Claims (9)

1. System for the automated launch from a carrier rockets of a portable anti-aircraft missile system (MANPADS) of the Igla type, containing launch modules (PM), each of which includes a hollow power beam with load-bearing supports, centering elements for mounting on a carrier and with clamps for fixing on the sides of the beam of launch tubes with missiles from the MANPADS, missile deployment mechanisms, protective front covers with mechanisms for opening them, while each PM has a gas supply line through the inlet fitting of compressed gas to the optical homing head (OGS) missiles and electro-pneumatic valves (EPC), means for connecting missiles to the PM, a remote control (PDU) with a communication unit, as well as the PM control electronics located in the cavity of the beam, characterized in that an electronic control module and communications (MUiS), connected to the remote control and electrically connected to each PM, while all PM are equipped with receiving devices for docking ground-based blocks of electro-gas power (NBP), the mechanisms of missile unstuck and the opening of the protective covers are made in the form of mon e-actuators, gas lines are connected via check valves to the receiving devices, each inlet fitting is equipped with a locking mechanism and is connected to the gas line through the rocket selection EPA, to the output of which the pneumatic actuator for opening the protective cover and the pneumatic actuator for opening the missile are connected via the additional EPK.  2. The system according to claim 1, characterized in that the M&S comprises a communication unit with a PM, a communication unit with a remote control, a PM selection and PM control unit, a command generation unit for the simultaneous descent of two missiles in salvo firing mode, a remote control request generation unit for the activation of the next NBP and missiles and the unit for generating a message on the remote control about the state of the PM and missiles, and the unit for selecting the PM and the PM control, the unit for forming the team for the simultaneous descent of two missiles in salvo firing mode, the unit for generating the request for the remote control for launching the next NBP and the missiles two-way communication with the remote control and launcher modules through the corresponding communication blocks and the remote control message generation unit, and the command formation unit for the simultaneous descent of two missiles in salvo firing mode, the remote control request generation unit for activating the next air defense system and missiles are additionally connected to the PM selection unit and PM management.  3. The system according to claim 1, characterized in that the bearing supports of each PM have center and bottom center and bottom elements for precise installation of several PM on the media with their location one below the other ("whatnot", "bunch"), as well as in rows.  4. The system according to claim 1, characterized in that each PM is equipped with devices for the electrical connection of missiles, made in the form of a guide spring-loaded casing with a centering hole.  5. The system according to claim 1, characterized in that the receiving devices for installing the NBP are equipped with spring cocking mechanisms and electromagnetic trigger mechanisms for opening the NBP sealing membranes.  6. The system according to p. 2, characterized in that the PM contains a control unit for capturing the target and launching the rocket, a block for delaying the launch of the rocket, a block for selecting and activating the NSP and EPK control, an MP control unit connected through a communication unit with two-way communication with the M&S and two-way communication with the control unit for capturing the target and launching the rocket, the unit for selecting and activating the NBP and EPK control and connected to the position sensors of the protective covers and the position sensors of the stoppers; a unit for selecting and activating an NPL and EPA control is connected to an EPC for selecting a missile and an EPC for connecting pneumatic actuators of missile deployment and to sensors for the presence of unused NBP; the missile launch delay unit is connected to the target capture and missile launch control unit and through the communication unit with the MUiS; the control unit for capturing the target and launching the rocket is connected with means for connecting launch tubes with missiles to the MP.  7. The system according to claim 6, characterized in that the position sensors of the protective covers and the position sensors of the stoppers comprise sequentially connected switching elements of the ignition circuit of the starting engine of the corresponding rocket.  8. The system according to claim 7, characterized in that each of the PM is equipped with a removable horseshoe-shaped check blocking the unauthorized opening of the protective covers. 9. The system according to claim 2, characterized in that it contains a unit for analyzing the angular velocity of the target, measured by means of PM and remote control.