RU2247927C2 - Combat section of guided missile - Google Patents

Abstract

FIELD: ammunition, in particular, combat sections of "air-to-air", "ground-to-air" guided missiles.

SUBSTANCE: the combat section of the guided missile is provided with four transceiving units and five AND gates located in a laser proximity fuse, the output of each transceiving unit is connected to one input of two respective AND gates, connected to whose second input is the output of the adjacent transceiving unit. The output of each AND gate is connected to the inputs of the signal processing unit, whose respective outputs via a safety-actuating mechanism are connected to six respective electric detonators of the initiating device located in six hitting members having shaped explosive charges with metal facings with a large corner radius on the end faces. Six hitting members and six receivers of reflected signals of the respective transceiving units re located symmetrically and uniformly in the parallel planes of the cross section in diameter with the longitudinal axes of symmetry perpendicular to the missile longitudinal axis in such a way that the plane formed by the longitudinal axis of the hitting member and the missile longitudinal axis is positioned at a similar distance from the two receivers of reflected signals adjacent to it. The invention provides for hitting of armored and usually air targets at misses up to 50 to 100 m due to a high kinetic energy of the "shaped nucleus" formed at blasting, oriented in the direction of the target of the hitting member.

EFFECT: enhanced probability of target hitting.

3 dwg

Description

The invention relates to the field of ammunition and can be used in aviation and anti-aircraft guided missiles to destroy air targets.

There are known combat compartments of guided missiles containing a cumulative-fragmentation warhead and an explosive device (See, Technical Description and Operating Instructions. The Strela-2M portable anti-aircraft missile system. -M.: Military Publishing House, 1971). The main disadvantage is that it requires a very accurate guided missile guidance system, because target defeat is carried out only with direct contact with the target, which does not allow the use of a non-contact fuse.

Currently, anti-aircraft and air-to-air guided missiles with warheads having warheads of high-explosive, high-explosive fragmentation and non-contact fuses providing remote detonation are used to destroy air targets. In missiles of this class, the main damaging factor is fragments. The main disadvantage of combat compartments in missiles of this class is that the radius of action of non-contact fuses is on average 5-15 m. This is due to the limited radius of the damaging effect of the fragments, which must have a certain kinetic energy at the moment of meeting with an air target

where: m _Osk is the mass of the fragment;

v _Osk - the speed of the fragment;

S is the area of the hole;

h is the penetration depth into the barrier;

E _c is the specific energy of displacing a unit volume of the material of the obstacle (See. Sargsyan RS Uncontrolled means of destruction. -M .; VVIA named after prof. N.E. Zhukovsky, 1980). To increase the radius of the damaging effect, it is necessary to increase the caliber and mass of the warhead, which is not always advisable.

Given the fact that there has recently been a tendency to increase the survivability of air targets, the combat compartments of guided missiles, which have rod warheads and non-contact fuses, have become widespread.

As the closest analogue (prototype), the combat compartment of an aircraft guided missile was selected (see RB Golyuk. Fundamentals of the theory and design of aircraft guided weapons. -Perm: Perm VATU, 1988. p. 33, 34, 47, 48). The combat compartment has a rod warhead (SBC), a laser non-contact fuse (LNV) and a safety-actuating mechanism. The striking elements of the UBC are steel rods of square cross section, tightly laid on the side surface of the cylinder, inside of which there are: a damper, explosive charge (BB) and a detonator located in the central tube. The laser non-contact fuse (non-contact optical fuse) of the active type has a transceiver device that includes two transceiver units (PPB), a signal processing unit (BOS), a power supply unit (PSU), an “I” circuit (coincidence cascade), and a safety executive mechanism (PIM). Under the influence of an explosive load pulse, the core cylinder expands at a speed of 1000-1200 m / s and forms a core ring with a continuously increasing radius. The core ring strikes a target encountered in its path. The radius of the ring reaches its maximum value at the time of complete expansion of the core cylinder, after which the ring loses its continuity and breaks into pieces.

The disadvantage is that the missile’s maximum miss (contact radius of a non-contact fuse) at 80% of the core ring continuity should not exceed 15 m.

The essence of the invention lies in the fact that the combat compartment of the guided missile is equipped with four transceiver units and five “I” circuits located in a laser non-contact fuse, the output of each transceiver unit being connected to one input of two corresponding “I” circuits, to the second the input of which is connected to the output of an adjacent transceiver unit, and the output from each “I” circuit is connected to the inputs of the signal processing unit, the corresponding outputs of which are connected to the safety-executive mechanism six corresponding initiating device electric detonators placed in six striking elements having shaped shaped-charge explosive charges with metal lining of large radius of curvature at the ends, and six striking elements and six reflected signal receivers of the respective transceiver units are located symmetrically and uniformly in parallel cross-sectional planes in diameter with the longitudinal axes of symmetry perpendicular to the longitudinal axis of the rocket in such a way that the plane formed by the longitudinal axis of the striking element and the longitudinal axis of the rocket is located at the same distance from two adjacent receivers of reflected signals.

This invention will allow to hit armored and conventional air targets at misses of up to 50-100 m. This will significantly reduce the requirements for accuracy of pointing the missile at the target, will make it possible to use simpler and cheaper homing systems while maintaining the given probability of hitting the target.

The invention is illustrated figure 1-3.

Figure 1 presents a block diagram of the combat compartment of a guided missile. The combat compartment consists of a housing in which a laser non-contact fuse (LHV), a warhead (warhead) and a safety-actuating mechanism (4) are located. VLF consists of a transceiver (PPU), which is six transceiver units (1), each of which includes a receiver and a transmitter. The transmitter consists of a laser emitter and an optical system. The reflected signal receiver includes an optical system, a photodiode and an amplifier. All six PPB (1) are installed symmetrically and uniformly in the VLF so that the angles between the optical axis of the POS in the equatorial plane are 60 °, while the angle of view of each POS in the equatorial plane is approximately 59 °. There are six “I” schemes in the LNW (2).

The outputs of two adjacent PPB (1) are connected to two separate inputs of each “And” circuit. The output from each “AND” circuit (2) is connected to the corresponding input of the signal processing unit (3) of the LNV.

The power supply unit (7) energizes the PUF, “I” circuits (2) and the signal processing unit (3). The corresponding outputs of the signal processing unit (3) are connected to the corresponding inputs of the autonomous safety-executive mechanism (4), the outputs of which are connected to the corresponding electric detonators (5) of the initiating device, which is part of the warhead (warhead). Each electric detonator (5) is placed in the explosive charge of the striking elements (6).

Figure 2 presents a section of the warhead of the combat compartment and the mutual placement of the damaging elements and receivers of the reflected signals PPB.

The warhead, which is six identical damaging elements (6), is located in the housing (9) of the combat compartment. Each striking element consists of a curly shaped cumulative charge of explosives (10) located in a metal shell (12), an end metal lining (11) with a large radius of curvature, an electric detonator (5) placed in an explosive charge near an end metal lining (11).

A central tube (13) with electrical wiring connecting the electric detonator (5) with the corresponding output of the safety-actuating mechanism is placed along the charge axis. All six striking elements are placed evenly and symmetrically in one plane, while the angle between the longitudinal axes of two adjacent striking elements is 60 °. The receivers of the reflected signals (8) of the transceiver units are also placed symmetrically and evenly in one plane parallel to the plane of placement of the damaging elements. The angles between the longitudinal optical axes of two adjacent receivers of the reflected signals are also 60 °.

Figure 3 for explanation presents the main types of projection and the main sections of the striking element:

a) top view;

b) front view;

c) bottom view;

d) view on the right (left);

e) and f) - sections of the striking element, where 12 is a metal shell, 10 is a shaped shaped explosive charge, 11 is an end metal lining of a large radius of curvature, 5 is an electric detonator, 13 is a central tube.

The combat compartment of a guided missile operates as follows. When the rocket is launched, after the power unit enters the mode, ± 27 V is supplied to the LNV power supply unit. The power supply unit (7) of Fig. 1 gives a stabilized voltage to the signal processing circuit and the transceiver. All six pulsed laser emitters of the transceiver units (1) of FIG. 1 are launched. For the normal functioning of the combat compartment, the rocket in flight rotates at an angular speed of approximately 5-10 r / s. When approaching the target, the homing head issues an “cocking-2” command to the VLF, from this moment the VLF is ready to issue a response signal to the PIM (4) of Fig. 1.

When the target is simultaneously in the field of view of two adjacent receivers of the reflected signals, from the outputs of the corresponding PPB, the amplified signals are simultaneously fed to the input of the corresponding “I” circuit, the output of which is connected to the signal processing unit, which with a certain delay gives an electric signal to the corresponding PIM input. Upon receipt of an electric signal from the PIM, to increase the active mass of the explosive, the initiation of the striking element oriented in the direction of the target is carried out from an electric detonator located in the explosive charge of the opposite striking element. When undermining, a cumulative core is formed, having a speed of about 2750 m / s, with a mass of the damaging element of 0.5 kg. In this case, the kinetic energy is 10 times higher than the kinetic energy of a 30-mm artillery shell.

Claims (1)

The combat compartment of a guided missile containing a warhead consisting of a body, explosive, striking elements, an initiating device, an active type non-contact laser fuse consisting of a transceiver device including two transceiver units, a power supply unit, a signal processing unit, an “I” circuit, and safety-actuating mechanism, characterized in that it is equipped with four transceiver units and five “I” circuits located in a laser non-contact fuse, with the output of each the receiving-transmitting unit is connected to one input of two corresponding “I” circuits, the second input of which is connected to the output of the adjacent transceiving unit, and the output from each “I” circuit is connected to the inputs of the signal processing unit, the corresponding outputs of which are connected to the safety-executive mechanism six corresponding initiating device electric detonators located in six striking elements having shaped shaped cumulative explosive charges with metal cladding rounding off the ends, with six striking elements and six reflected signal receivers of the respective transceiver blocks located symmetrically and uniformly in parallel planes of the cross-section in diameter with the longitudinal axis of symmetry perpendicular to the longitudinal axis of the rocket so that the plane formed by the longitudinal axis of the striking element and the longitudinal the axis of the rocket, located at the same distance from two adjacent receivers of reflected signals.

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