RU2206041C1 - System for automated launching of rockets from portable antiaircraft rocket complex of "igla" type - Google Patents

Abstract

FIELD: launchers of ground-, air- or surface-based rockets. SUBSTANCE: realization of this system enables rockets to be launched both under mode of salvo and single-shot fire from various types of carriers. Proposed system is supplemented with electron module for communication and control connected to remote control desk and electrically coupled to each launching module. All launching modules are equipped with intake devices to mate ground units of electric and gas supply. Mechanisms which unlock rockets and open protective covers come in the form of air-operated drives. Gas mains are linked to intake devices through check valves. Each feeding pipe union is provided with fixing mechanism and is joined to gas main through electric-pneumatic valve for selection of rocket to which outlet air-operated drive opening protective covers is linked and air-operated drive unlocking this rocket is connected through additional electric-pneumatic valve. EFFECT: capability to launch rockets under mode of both salvo and single-shot fire. 8 cl, 7 dwg

Description

 The proposal relates to ground, air or surface-based launchers and can be used to launch missiles in launchers 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 missile, see RF patent 2088877, issue nny on application 95119765, IPC 6 41 A F 23/34, F 41 F 3/04.

 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 launches directly by the operator, as well as when the need arises, their use without any changes to launch from the operator’s shoulder. Not for use with an air vehicle.

 The known complex "Mistral" is a helicopter-based, containing one or two launchers on board the helicopter, each 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 provides interaction between missiles and helicopter weapon systems, see V. Viktorov, French Mistral air defense systems, Foreign Military Review, 1987, 4, Aviation Week, 1985, v. 122 , 2, p. 70; Prospect of the Mistral air-to-air complex by MATRA DEFENSE; NTI, 7-8, 1996, c. 46-49.

 The closest analogue (prototype) is an air-based launch module (PM) according to US patent 4429611, IPC F 41 F 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 mount using means of connection with the power supply system and the cooler supply 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 both sides of the central channel and are located in two pillars equipped with locks (clamps) - front and rear. Each front lock consists of a fixed tool tray and a movable element, which is held in position by the thumb screws. The movable elements are adjacent to the fixed tool holders and open outward in such a way that access to the launch tubes from the sides is provided.

 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 PM, standing on 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 electronic controls and triggering means for launching the corresponding rocket through cable communication with the operator’s console in the cockpit of the aircraft, which allows the pilot or operator to launch the 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 successive launches from air carriers of missiles of this kind (Stinger), cannot be used for launches of widespread missiles from MANPADS of the Igla type 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 is actually 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 electric-gas power units) both in single-shot mode and in multiple rocket-launch mode with two missiles simultaneously simplifying the operator’s work by transferring individual missile launch operations 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 vehicle, armored personnel carrier, boat, with minimal modifications to the system associated with the conditions for its specific placement on the carrier, and also allows the use of regular air defense from the infantry 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 electric gas supply units (NBP), rocket unlocking mechanisms and protective cover rotation are made in the form of pneumatic actuators, gas lines are connected via check valves to receiving devices, each supplying sleep nipple It 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, the mechanism for opening 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 control 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 the noise immunity during automatic target capture and during volley fire. The PM control electronics contains 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 pneumatic drive electronic control devices protective covers, EPC 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 the electrical docking of missiles are made in the form of a spring-loaded guide casing with a centering hole. The bearing supports of each PM have bottom and top centering elements for precise installation of several PMs on the carrier 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.

 In FIG. Figure 1 shows a block diagram of a system for the automated launch of missiles of the Igla type, figure 2 shows a general view of a PM, figure 3 shows a functional diagram of a PM, figure 4 shows a general view of receiving devices for connecting an air defense system, and figure 5 - a General view of the device for the electrical docking of launch tubes from MANPADS with missiles, Fig.6 is a General view of the mechanism of rassoporeniya missiles and a General view of the inlet fitting, Fig.7 - General view of the protective front covers and checks.

 The proposed system (see figure 1) for the automated launch of missiles from MANPADS of the type "Needle" includes from one to several PM 1 (preferably at least two). Figure 1 shows for example 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 (Zap NBP) for activating the NBP, button 6 (RPM) for issuing the command "Permission to launch missiles." It is preferable to use buttons for these control commands, as short-term commands are issued using them. A longer command will be from 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 (BSv remote control MUiS) for connecting to MUiS 2. Through this unit two-way communication (preferably in the form of a serial asynchronous communication line) MUIS and remote control exchange information signals in a known manner. The remote control can 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 the target parameters to media devices from the media devices.

MUIS contains:
two-way communication unit 10 (BSv MUiS remote control and BforSoobsch on remote control) with a remote control, which includes a block for generating messages on the remote control;
two-way communication unit 11 (BSv MUiS PM) 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 from the PM 1 at the output.

 To work with carriers that have blocks that provide 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 the PM 1 and from the media through the remote control from the block 9.

 Blocks 6, 10, 11, 12, 13, 16 are made on microcontrollers of the 1830BE51 type. Examples of various blocks using microcontrollers are given, for example, in the book of V.V. Stashin, A.V. Urusov "Design of 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, Fig.3, 6 (not included in the PM), from MANPADS. The PM is equipped with mechanisms for unlocking missiles 23 (Mon Priv of the stop), protective front covers 24 with mechanisms for opening them in the form of pneumatic actuators 25 (Mon Priv of the cap), while each PM has a gas supply line 26 through the inlet fitting 27 of compressed gas to the optical homing head ( OGS) missiles from electro-pneumatic valves (EPC) 28 and is equipped with means for electrical connection of 29 launch tubes with missiles to PM. In the sealed cavity of the power beam 18 is placed the control electronics PM. Bearing supports 19 have fastening and centering elements 20 both above and below, allowing the PM to be mounted both on the carrier and between each other (one above the other), in the form of a “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 support legs 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 NBP 31 (figure 3, 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 includes a control unit 34 (BUG control and Rocket Launch) for target acquisition and missile launch, block 35 (BZaderStartRocket) missile launch delay unit, block 36 (Selection and Activation NBP UprElPnevKlap) for selecting and activating the NBP and EPK control, block 37 (BU) PM control, connected through the block 38 (BSv PM MUiS) communication PM MUIS two-way communication with MUiS 2 and two-way communication with block 34 control capture of the target and missile launch, block 36 of the selection and activation of the NPL and EPA control. The start-up module is equipped with position sensors 39 of the protective covers and position sensors of the stoppers 40. The NBP selection and activation unit 36 and the EPA control unit are connected to the rocket selection EPK 28 and the EPK 33 for connecting pneumatic actuators of missile deployment 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 to means for connecting 29 missiles in the launch tubes to the PM and has means for detecting the presence of the rocket on the PM, for example, in the form of a closed circuit through the rocket, which 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 communication unit 38 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 of the 1830BE51 type.

 In the current embodiment, the four receiving devices 30 shown in FIG. 4 are structurally implemented in a single unit mounted on 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 and an electrical connector are connected for connecting power supply 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 respective 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.

 At the front end of the PM (see figure 2), a horseshoe-shaped safety pin 44 is installed that blocks the unauthorized opening of the protective front covers and, therefore, blocks 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 Fig. 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. An electrical connector provides electrical communication between the control electronics through the launch tube and 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 elements of the electrical connector and the connection of the electric circuits of the rocket to the control electronics.

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

 The control unit 34 for capturing the target and launching the rocket was borrowed from the Igla MANPADS (Igla portable anti-aircraft missile system (9K38), (Moscow, Military Publishing House, 1987, p. 50)) and is designed to prepare the missile for launching, capture the target and supply voltage to the launch circuit of the rocket. This block carries out the spinning of the gyroscope rotor of the OGS gyrocoordinator, automatic locking and snapping, processing and evaluation of signals from the rocket when the target is captured by the 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 missile stopper and connects the starter motor circuit to the unit 34 for controlling 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;
- equipment of the system with missiles in launch tubes from MANPADS and PM NBP equipment from MANPADS;
- turn on the system (standby mode);
- combat work.

 Basically, as the remote control 3, the display controls are already available on the media. 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 missile in the pipe from the MANPADS of the type "Needle" stack, being on the 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, providing a "lowering" of the launch tube pin into the centering hole 46 of the guiding cover 45. The clamps on the front and rear supports are successively lowered and the locks are fastened, the inlet fitting 27 is inserted into the hole of the rocket launch pipe 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 - demarcation. 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 a sub-stage of combat work.

 At the beginning of combat work (duty) with 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 MUIS 2 and PM. Through secondary power supplies PM 42, power is supplied to the PM units. The MUIS block 12 through the MUiS communication unit 11 with the PM sequentially, periodically polls the PM on the 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. This 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 begin 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 to prevent 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 with a resource for work, and issues a command to the selected PM to start work. PM, having received a command to the PM control unit 37 from the communication unit 38, issues a command to the block 36 for selecting and activating 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 power supply to the electromagnet of the trigger mechanism of the receiving device 30 NBP causes the trigger to trigger, which produces the opening of the NBP, while 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, 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 rotor of the gyroscope coordinator OGS, processing and evaluates the signals received from the rocket when the target is captured from the OGS, and if there is a command to enable launch from button 6 or a command replacing it from block 9 of the remote control, it automatically resolves the OGS gyrocoordinator and issues to the PM control unit 37 a message about the readiness of this missile to start the launch program (charging the onboard power supply of the rocket in flight mode, charging the warhead, removing the cancer you are off the stop, applying power to the rocket's starting engine).

 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 the remote control unit 9 through the block 12, delays the start of the missile launch program (through the PM missile launch delay block 35) with the first one that captured the target until the target was captured by the second missile or the specified waiting time ended. For simultaneous launch of missiles, this is necessary, for example, to prevent smoke from blocking the engine of one rocket from the line of sight to the target of another rocket, the command to remove the delay in launch is sent simultaneously to all missiles. Block 35 delay the launch of the rocket removes the delay if the rocket is ready to start the launch, and prohibits the launch of the rocket in this cycle of operation, 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 button 6 of the remote control and pressing it again and repeating the cycle of capturing the OGS target.

 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 missile 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 (it is an accessory of the launch tube). 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 missiles, which include Igla-type MANPADS. The magnitude of the angular velocity of the target is usually measured and the media. Block 16 compares these angular velocities with each other and gives out to block 12 a message about the starting modules at which angular velocities exceed 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 the system for the automated launch of Igla MANPADS. Currently, one of the prototype models has successfully launched missiles of the Igla complex on target.

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 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 via 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 and through an additional EPA-pneumatic actuator for uncoupling this rocket are connected.  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 the PM through the corresponding communication blocks and the message generation unit on the remote control, 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.  3. The system according to claim 1, characterized in that the supporting supports of each PM have centering elements from below and above for precise installation of several PMs on the carrier 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 EPA control, the PM control unit, connected through the 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 NBP selection and pickup unit and the EPA control, and connected to the protective cover position sensors and the stop position sensors, the NBP selection and activation block and the EPK control unit is connected to the rocket and EPK selection EPK connecting pneumatic actuators for missile deployment and with sensors for the presence of unused NBPs, the missile launch delay unit is connected to the target acquisition and missile launch control unit and through the communication unit with the MUiS, the target acquisition and missile launch control unit is connected to the means for connecting launch tubes with missiles to the PM.  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.

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