RU2247313C1 - Tail section of guided missile - Google Patents

Abstract

FIELD: guided missiles, applicable in the constructions of anti-tank missiles launched from launching packs with low initial speeds.

SUBSTANCE: the wire communication line in the tail section of the guided missile is made in the form of a control microcable wound on the body of the booster engine. The inner end of the microcable connected to the control compartment. Installed on the body of the booster engine is a protective screen protecting the control microcable against damage at ignition of the tracer pyrotechnic compound. The height of the protective screen is commensurable with the height of the control cable winding, and its area exceeds the tracer burning area formed during the time period from the moment of launching to deployment of the stabilizers.

EFFECT: enhanced adaptability to manufacture, strength, electric insulation and operating characteristics of the rocket, and simplified construction of it.

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Description

The invention relates to the field of guided missiles and can be used in the construction of anti-tank missiles launched from launch containers with low initial speeds.

Known tail compartment with a PLC coil and stabilizer block guided missile 9M116 complex "Metis", adopted as a prototype [1].

Structurally, the prototype (Fig. 1) consists of a frame (1), on which a two-wire wire (2) is wound, a block (3) fixed to the frame with two screws (5) and used to connect the PLC to the wire (4), through which control signals to the steering unit. The external output of the wire communication line is made in the form of a cable (6), ends with a contact plug (7) and serves for mechanical and electrical communication of the PLC with the transport launch container. The stabilizer block (8) consists of 3 consoles mounted with clamps on the engine casing, and a pyrotechnic tracer (9) is installed on one of the console in the clamp. The prototype wire contains conductors of electric current in the form of insulated conductive conductors, the conductors are isolated from each other and enclosed in a shell.

Modern conditions for the use of anti-tank missiles have required the creation of such a technical solution that would overcome:

- insufficiently high breaking strength, which does not allow the use of high speeds when unwinding such cables;

- the complexity of the technological process of manufacturing cables of this design;

- the lack of the possibility of firing from the edge of the water at maximum range;

- loss of performance under the influence of ultimate tensile loads;

- dynamic impact of the wire on the inner radius of the flange at the rear cone of the winder when winding the last three layers of the wire;

- a large number of related parts and high requirements for their manufacture and combination;

- the lack of protection of the winding of the PLC coil from damage during ignition of the pyrosostructure of the tracer.

The objective of the invention is the creation of the tail compartment of a guided missile with high strength, operational, thermoresistive characteristics, a simplified design and high manufacturability.

The problem is achieved in that in the tail compartment of a guided missile containing a starting engine, a stabilizer block, a wired communication line (PLC), a pyrotechnic tracer, the new one is that the PLC is made in the form of a control microcircuit wound on the body of the starting engine, while the end of the microcable is connected to the control compartment, a protective shield is installed on the housing of the starting engine, which protects the PLC control microcable from damage during ignition of the trace composition of the tracer, the height of The protective screen is commensurate with the winding height of the PLC control microcable, and its area exceeds the burning area of the tracer, which is formed during the time from the start to the opening of the stabilizers.

Figure 2 shows the design of the proposed technical solution for the tail compartment of a guided missile.

The control microcable (11) is wound directly on the housing of the starting engine (10), to which the stabilizer arms (8) are also attached. This design allows you to increase the mechanical strength of the camera starting engine, because at the time of maximum loads on it (at start), the control microcable is a power structure. The inner end of the winding of the control microcable is brought out to the socket (12) for electrical connection through the harness (13) with the control compartment. Moreover, this connection is detachable, which ensures higher manufacturability, maintainability, efficiency and reliability. The outer end of the winding micro control cable ends with a cable (6) and a four-pin plug (7). The plug is used to connect the PLC to the ground control equipment and is inserted into the corresponding slot on the transport and launch container. The presence of a protective screen (14) ensures the protection of the PLC control microcable from damage at the moment of ignition of the tracer pyrocomposition (9). It does not allow combustion products to directly affect the control microcable, and the height of the protective shield is commensurate with the height of the winding of the PLC control microcable, and its area exceeds the burning area of the tracer from the time of start to the opening of the consoles. The angles of the front and rear cones of the coil winding were empirically selected to ensure a uniform and trouble-free process of winding the PLC control microcable during operation of the product and, respectively, are 155 and 157 °.

The stabilizer consoles are in the transport and launch container when folded. The pyrotechnic tracer is located between the starting engine chamber and the console on which it is mounted. At the moment of launching the rocket, the force of gases from the starting charge through the gas outlet to the end of the tracer ignites the pyrotechnic composition. At the same time, the protective shield does not allow the combustion products to act on the PLC microcontrol cable of the tail section. After the rocket leaves the transport and launch container, the layer-by-layer winding of the PLC control microcable begins, along which control signals are sent to the rocket.

In the manufacture of the PLC control microcable, it is possible to use a copper wire rod, from which conductive conductors are used, which serve as conductors in it. The socket consists of a printed circuit board with conductors deposited on it and capacitors protecting the wiring of the starting motor from electromagnetic fields, as well as contact leads in a plastic shell. The protective screen is made in the form of a metal plate and mounted on the housing of the starting engine without gaps.

The proposed design of the tail compartment of the guided missile allows you to:

- reduce the number of parts of the tail compartment of the guided missile, which allows to increase the manufacturability of its production and reduce the cost, increase the tensile force by 1.5 times, remove the collar from the rear cone of the winder, which avoids the dynamic impact of the wire on the inner radius of the collar when winding the last three layers of control micro cable;

- significantly increase the reliability of the PLC at the time of launch due to the presence of a protective screen;

- to ensure the preservation of the maximum diameter of the control microcable (in tension) within 0.33 mm - 0.35 mm;

- place more wire;

- eliminate soldered joints when connecting the PLC to the control compartment, which allows to increase the manufacturability of its production.

The use of this design of the tail compartment on guided missiles of the Metis-M1 anti-tank missile system allowed:

- increase the reliability of the product during flight at maximum range;

- increase the flight speed of a guided missile due to an increase in tensile strength;

- to ensure operation under conditions of constant exposure to sea water at temperatures from minus 50 ° C to plus 60 ° C;

- to provide the possibility of firing over the edge of the water at maximum range;

- increase the effectiveness of hitting a target.

Sources of information

1. Guided missile 9M116. Technical description and instruction manual. M. Military Publishing House, 1980

Claims (1)

The tail compartment of a guided missile, containing a starting engine, a stabilizer block, a wired communication line (PLC), a pyrotechnic tracer, characterized in that the PLC is made in the form of a micro control cable wound on the housing of the starting engine, while the inner end of the micro cable is connected to the control compartment, on the starter motor housing has a protective shield that protects the PLC control microcircuit from damage during ignition of the trace composition of the tracer, and the height of the protective shield is commensurate with the height of the windings microcable CLV control, but its area exceeds the tracer combustion area, formed during the time from the start until stabilizers disclosure.

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