RU2551831C1 - Missile unit of jet-propelled projectile - Google Patents

Abstract

FIELD: armaments and ammunition.

SUBSTANCE: missile unit of jet-propelled projectile contains engine with nozzle, opening blades, and shell with boosting assembly. The shell boosting assembly is made in form of rupture ring with bonding jumpers with calibrated rupture force, and is connected with the engine nozzle. The bonding jumpers are made in the rupture ring, on which from one side (external), and from another side (internal) threads are made for connection with shell and nozzle, respectively. On the external and internal surfaces of the rupture ring the cone areas are made, they respectively interact with cone areas made congruently on the shell and nozzle. H-shape windows are made in the rupture ring between the bonding jumpers. The shell is provided with damper in form of the ring corrugation.

EFFECT: reduced weight, increased reliability and safety during launching and operation of the shell.

5 cl, 2 dwg

Description

The invention relates to the field of rocket technology, namely to the rocket parts (RF) of rockets (PC) multiple launch rocket systems, and can find application in the development of new models of shells for multiple launch rocket systems for land and sea based, as well as aircraft missiles.

When airborne or sea based, the presence of discarded projectile elements becomes of paramount importance, because they may damage the glider of an airplane, helicopter or ship superstructure. Therefore, there is the problem of creating an RF of a fairly simple and reliable design, universal for use in various types of media. The best option is the RF design, which does not have discarded projectile elements when starting the engine.

Known rocket missile, see, for example, the manual "Orlov A.R. Fundamentals of the design and operation of shells of multiple launch rocket systems, Tula, 2002, p.143-145 ", consisting of an engine with a nozzle, expanding blades and a contact cover. The blades in the closed position are held by the ring, and the projectile is held in the launcher by a spring-loaded locking mechanism, which at start releases the drive pin on the nozzle block, the contact cover and ring being discarded. A similar design is widely used in ground-based reactive systems, where the presence of discarded projectile elements is not of particular importance.

The closest in technical essence and the achieved technical result is the missile part of the rocket according to the patent of the Russian Federation No. 2258890, F42B 10/14, publ. 08/20/2005, adopted by the authors as a prototype, containing an engine with a nozzle, expanding blades and a sleeve with a forcing unit.

After the engine is started, when the required thrust parameters are reached, which correspond to the forcing force, the shell rolls open and the projectile begins to move, while the missile part of the shell is separated from the shell, which remains in the guide of the gun block.

This design eliminates the need for discarded projectile elements and allows the use of PCs from airplanes and helicopters. The design of the sleeve mounted on the outer surface of the nozzle by rolling is quite simple and is used in unguided aircraft missiles.

The reasons that impede the achievement of the technical result indicated below when using the well-known RF PC adopted by the authors for the prototype include the fact that this design is not reliable enough, since it does not provide the required range of forcing forces, since the rolling opening parameters have a large spread. Reducing the force of forcing leads to undocking and falling out of the projectile from the guide block of the guns during transport overloads, for example during take-off and landing of an aircraft. The increase in forcing forces leads to a jam in the guide in the guide block of the guns at launch due to non-disclosure of rolling. Both cases reduce the reliability and safety of a missile and can lead to an emergency.

Thus, the objective of this technical solution (prototype) was to ensure the separation of the projectile from the liner when starting the engine.

Common signs with the design of the missile part of the rocket proposed by the authors is the presence in it of an engine with a nozzle, expanding blades and a sleeve with a forcing unit.

In contrast to the prototype, in the design of the rocket part of the rocket proposed by the authors, the cartridge forcing unit is made in the form of a rupture ring with jumpers with a calibrated breaking force and fastened to the engine nozzle.

In particular cases, i.e. in specific forms of execution, the invention is characterized by the following features:

- jumpers are made in a rupture ring, on which, on the one hand, on the outer, on the other, on the inner surfaces, threads are made for connection with the sleeve and the nozzle, respectively, while on the outer and inner surfaces of the rupture ring there are conical sections correspondingly interacting with conical sections made congruently on the sleeve and on the nozzle;

- in the rupture ring between the jumpers made H-shaped windows;

- the sleeve is equipped with a damper;

- the damper is made in the form of an annular corrugation.

It is this that 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 result.

These signs, distinctive from the prototype and to which the requested amount of legal protection applies, are sufficient in all cases.

The objective of the invention is to increase the reliability and safety of the missile part of a rocket during its launch and operation, as well as reducing the mass of the shell by reducing the mass of the shell.

The specified technical result in the implementation of the invention is achieved by the fact that in the known design of the RF PC containing the engine with the nozzle, the expanding blades and the sleeve with the forcing unit, the feature is that the forcing unit of the sleeve is made in the form of a rupture ring with jumpers with a calibrated breaking force and bonded to the engine nozzle.

A new set of structural elements, as well as the presence of connections between them, allows, in particular, due to the fact that:

- the sleeve forcing unit is made in the form of a rupture ring with jumpers with a calibrated breaking force and fastened to the engine nozzle, to reduce the dispersion of the force forcing, which leads to an increase in the reliability and safety of the use of the missile part of the rocket during its launch and operation.

Signs characterizing the invention in specific forms of execution, allow, in particular, due to the fact that:

- jumpers are made in a rupture ring, on which, on the one hand, on the outer, on the other, on the inner surfaces, threads are made for connection with the sleeve and the nozzle, respectively, while on the outer and inner surfaces of the rupture ring there are conical sections correspondingly interacting with conical sections made congruently on the sleeve and on the nozzle, eliminate radial gaps and reduce the radial vibration load on the jumpers, which leads to an increase in the reliability and safety of RF PC application When it is started and operation;

- in the rupture ring between the jumpers made H-shaped windows, to reduce the mass of the sleeve and, accordingly, to reduce the mass of the projectile;

- the sleeve is equipped with a damper, to reduce axial dynamic loads during transportation of the projectile in the gun block and to increase the reliability and safety of operation of the RF PC during its launch and operation;

- the damper is made in the form of an annular corrugation, to ensure uniform load distribution on the jumpers.

The essence of the invention lies in the fact that in the known design of the rocket part of a rocket containing an engine with a nozzle, expanding blades and a sleeve with a forcing unit, in contrast to the prototype, according to the invention, the forcing unit of the sleeve is made in the form of a rupture ring with jumpers with a calibrated breaking force and bonded to the engine nozzle.

The essence of the invention is illustrated by drawings, where in Fig.1 shows a General view of the rocket part of a rocket, in Fig.2 - node connection rupture ring with a nozzle and a sleeve.

The proposed missile part of the rocket contains an engine 1, a nozzle 2, a drop-down blade 3, a sleeve 4 with a forcing unit 5, a rupture ring 6 with jumpers 7. A damper 11 is made in the form of an annular corrugation on a cylindrical section of the sleeve 4. In the closed position, the opening blades 3 are blocked by a sleeve 4. On the outer surface of the nozzle 2, a rupture ring 6 is installed until it stops in a conical section 8. On the external thread of a rupture ring 6, a sleeve 4 is installed all the way into a conical section 9. Between the jumpers 7 in the rupture ring 6 has H-shaped windows 10. The missile part of the rocket is mounted and fixed in the guide 12 of the gun block.

The missile part of the rocket operates as follows.

After starting the engine 1 when reaching the required thrust parameters corresponding to the force of forcing, the jumpers 7 of the rupture ring 6 break, and the projectile begins to move in the guide 12 of the gun block. The sleeve 4 with a part of the rupture ring 6 remains in the guide 12, a part of the rupture ring 6 remains on the thread of the nozzle 2 of the engine 1, and the opening blades 3 are kept from opening by the walls of the guide 12. When leaving the guide 12, the blades 3 open.

The use of the missile part of the rocket in accordance with the invention provides increased reliability and safety of the projectile during its launch and operation, as well as a decrease in the mass of the projectile by reducing the mass of the shell.

Currently, in accordance with the invention, design documentation has been developed for the design of a missile part of a rocket. In accordance with the documentation, a sample of the device was manufactured, successful tests were carried out, confirming the operability of the created technical solution.

Claims (5)

1. The rocket part of a rocket containing an engine with a nozzle, expanding blades and a sleeve with a forcing unit, characterized in that the forcing unit of the sleeve is made in the form of a rupture ring with jumpers with a calibrated breaking force and fastened to the engine nozzle. 2. The missile part according to claim 1, characterized in that the jumpers are made in a rupture ring, on which, on the one hand, on the external, on the other, on the internal surfaces, threads are made for connection with the sleeve and nozzle, respectively, while on the outside and conical sections are made on the inner surfaces of the rupture ring, respectively interacting with conical sections congruently on the sleeve and on the nozzle. 3. The missile part according to claim 1, characterized in that in the rupture ring between the jumpers made H-shaped windows. 4. The missile part according to claim 1, characterized in that the sleeve is equipped with a damper. 5. The missile part according to claim 4, characterized in that the damper is made in the form of an annular corrugation.

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