RU2448321C1 - Missile - Google Patents

Abstract

FIELD: weapons and ammunition.

SUBSTANCE: missile comprises a nose fuse, a warhead and a jet engine of solid fuel with a contract device made in the form of a cover closing an output section of a nozzle. The side surface of the cover is equipped with a local lug directed towards the jet engine, at the same time the contact sector is placed in the lug body, and the cover end is formed with joined stiffening ribs with weakened areas between them.

EFFECT: higher safety of missile handling.

3 dwg

Description

The present invention relates to the field of rocket technology, namely to rockets (PC) and can find application in the development of new models of PCs for multiple launch rocket systems (multiple launch rocket systems) land and sea based.

To ensure the launch of the PC equipped with a contact device that provides the docking of electrical circuits of the launcher (PU) and the projectile. An electric pulse is transmitted from the contact of the PU through the contact device of the projectile to the electric igniter, which through the igniter activates the powder charge of the rocket engine. When the set pressure is reached in the engine chamber, the plug located in the nozzle block and providing the necessary forcing force is discarded, and the PC starts moving along the guide.

At the start of the PC, a hot gas jet washes the contact of the launcher, causing erosion, which over time can lead to disruption of the electrical connection between the launcher and the projectile. This circumstance leads to the need for routine maintenance - replacing worn out contacts of the launcher.

Known PC described in the book Kurov V.D., Dolzhansky Yu.M. "Fundamentals of the design of powder rocket shells", Oborongiz, M., 1961, p. 202. It consists of a head fuse, a warhead, a solid fuel rocket engine (solid propellant rocket engine) and a contact device located in front of the engine.

The contact device transmits an electrical impulse to the pyro-candle, which uses the solid-propellant igniter. In this case, the contact device at the start of the PC and in flight remains in front of the engine. Contact PU remote from the rear end of the guide to the length of the motor PC. In the nozzle block is a stub that is discarded at the start of a rocket.

The described shells are launched from the launcher, consisting of rail guides arranged in a row, which provides easy access to the launcher contacts for replacement if they burn out during operation. At the same time, the PU under consideration provides a low loading density, and therefore low combat efficiency, since the number of PCs in a salvo is limited by the number of guides in a row.

Thus, the noted limitations are significant disadvantages of the PC design in question.

The objective of this technical solution (analogue) was to develop a PC fairly simple and reliable design. Common features of the analogue with the proposed authors of the PC are the presence of a head fuse, warhead, solid fuel rocket engine and contact device.

An optimal PC design providing a high charge density would be a PC design with a contact device located in the rear of the engine and extended beyond the rear end of the guide, in which case there is no difficulty replacing the PU contact.

The closest in technical essence and the achieved technical result is the PC described in the book "Combat vehicle 9P138. Technical Description and Operating Instructions ”, part 3, book. 1, Military Publishing House M., 1986 ". It consists of a head fuse, a warhead, a solid fuel rocket engine and a contact device in the form of a cover with a contact sector. The cover is fixed to the nozzle block cut and is reset when the preset pressure value in the engine chamber is reached.

The guides are located on the PU in several rows, which significantly increased the loading density, and therefore the combat effectiveness of the system. It is not possible to position the contact device in the front of the engine with this design of the control unit, because Replacing burned-out contacts will require overhaul of the entire package of rails to access the contacts located in the upper rows.

Based on the foregoing, the PU contacts are placed beyond the rear cut of the guides, which makes it convenient to replace them with wear, and the contact device PC is located on the cut of the nozzle block.

At the time of starting the rocket engine, the pressure created by the products of fuel combustion throws the cover away from the nozzle block PC in the direction of action of the jet. At the same time, it is impossible to predict the direction of its movement, as well as the number of fragments into which it collapses when it hits an obstacle. The use of such a design of the contact device requires an increase in the size of the security zones to exclude damage to personnel, equipment and other objects by fragments of the contact device when starting the PC.

Such a contact device, simple in design and highly reliable, is widely used in the development of ground-based PCs. At the same time, a significant mass of a cover with a contact sector flying off at the launch of a missile projectile significantly increases the size of the safety zone, imposes restrictions on the placement of PCs on sea and air carriers because of the possibility of damage to deck superstructures of a ship or boat, helicopter glider or airplane, which is completely unacceptable .

Thus, the known PC (prototype) has significant disadvantages:

- a significant mass of parts of the contact device flying off at the start of the PC prevents the placement of a rocket on sea and air carriers;

- the unpredictable direction of flight of the contact device at the start of the PC can lead to damage by flying parts of the calculation of the combat vehicle located in the vicinity of equipment and other objects.

The objective of this technical solution was to increase the combat effectiveness of the system by increasing the loading density of the guide package, but not having sufficient versatility to use rockets.

Common features with the proposed authors of the PC are the presence of a head fuse, warhead, rocket engine of solid fuel with a contact device, made in the form of a cover that overlaps the exit section of the nozzle.

In contrast to the prototype, in the proposed PC, the side surface of the cap overlapping the outlet section of the nozzle is additionally provided with a local tide directed toward the jet engine, the contact sector being placed in the body of the tide, and the end face of the cap formed by interconnected stiffeners with weakened sections between them .

This is what allows us to conclude that there is a causal relationship between the totality of the essential features of the claimed technical solution and the achieved technical results.

The indicated features that are distinctive from the prototypes and to which the requested amount of legal protection applies are sufficient in all cases.

The objective of the invention is to increase the safety of combat use of the PC and expand the possibility of its use both on land carriers and on sea-based carriers (ships, boats) by crushing the contact cover into small fragments when it is torn and hit the barrier, as well as giving it directional movement.

A new set of structural elements, as well as the presence of connections between parts, allow due to the following:

- ensure that the contact sector in the body of the tide on the side surface of the contact cover when charging the PC into the launch oriented orientation of the tide of the contact cover, which is the eccentricity of the mass and allows you to give the cover directional movement after stalling, for example, to the ground;

- the end faces of the lid with interconnected stiffening ribs with weakened sections between them to ensure crushing of the contact lid into small fragments after breaking off the nozzle block and hitting an obstacle, which can significantly reduce the security zone during firing, as well as reduce the impact of fragments flying off at the start of the PC on nearby facilities.

The essence of the invention lies in the fact that in a rocket containing a head fuse, a warhead and a solid fuel rocket engine with a contact device made in the form of a cover that overlaps the nozzle exit section, in contrast to the prototype according to the invention, the side surface of the cover is further provided with directional towards the jet engine with a local tide, while the contact sector is located in the body of the tide, and the end face of the cover is formed by interconnected stiffeners with weakened dipper between them.

The invention is illustrated by drawings, where in Fig.1 shows a General view of the PC, Fig.2 is an enlarged view of the rear part of the solid propellant rocket engine, Fig.3 is a view of the PC from the side of the cover.

The PC consists of a head fuse 1, a warhead 2 and a solid fuel 3 jet engine with a contact device 4 (Fig. 1), made in the form of a cover 5, overlapping the output section of the nozzle of the nozzle block 6 (Fig. 2).

The side surface 7 of the lid is additionally equipped with a local tide 8 directed towards the jet engine, with the contact sector 9 placed therein (FIG. 2). The end face of the lid is formed by interconnected ribs 10 with weakened sections 11 between them (figure 3).

The projectile operates as follows.

When charging the PC, the contact sector interacts with the contact of the launcher, providing electrical communication between them. Since the contact sector 9 is placed in the body of the tide 8, which is the eccentricity of the mass, its orientation is provided in a given direction, for example, to the ground. An electrical impulse from the starting equipment is transmitted through the contact sector to the electric igniter 12 of the engine, which activates the ignitor 13, which ignites the charge of solid fuel 14 (Fig.2).

When the pressure in the chamber of the engine 3 (Fig. 1) reaches the set value, the contact cover 5 breaks off the nozzle block 6 (Fig. 2) and starts moving due to the location of the mass eccentricity. Under the influence of gas pressure, as well as when hitting an obstacle, the contact cover is destroyed in weakened sections 11 (Fig. 3) into several fragments.

After the contact cover is broken, the PC starts moving along the guide, and then along the path. Upon contact with the surface of the earth fuse 1 undermines the warhead 2 (Fig.1).

Using the proposed invention, design documentation was developed and a batch of shells for flight tests was made, which confirmed the indicated positive effect.

Claims (1)

A missile containing a head fuse, a warhead and a solid fuel rocket engine with a contact device made in the form of a cover overlying the nozzle exit section, characterized in that the side surface of the cover is additionally provided with a local tide directed toward the jet engine, while the contact the sector is located in the body of the tide, and the end face of the lid is formed by interconnected stiffeners with weakened sections between them.

Images