RU2806605C1 - Rotating rocket projectile launched from tubular guide - Google Patents

Abstract

FIELD: rocketry.

SUBSTANCE: rocket projectile launched from a tubular guide contains a block of stabilizers with blades placed on it, drive pins, a fairing, and a blade lock. The rocket projectile is also equipped with a rotating fairing of the stabilizer unit, on which a support with a base and a stop is mounted, having an angle of inclination of 18-20° to the cross-sectional plane of the projectile. The support is located at a distance of 0.005-0.02 times the projectile calibre from the axis of the driving pins. The outer diameter of the support does not exceed the calibre of the projectile.

EFFECT: reliable fixation and exclusion of reverse movement of the projectile from the tubular guide after loading and during combat work.

2 cl, 3 dwg

Description

The invention relates to the field of rocketry, namely to guided missiles of multiple launch rocket systems.

The object of the invention is a guided missile, launched from a tubular guide, with increased accuracy and firing range, ensuring reliable fixation in the tubular guide after loading and during combat operation.

It is known that one of the ways to solve the problem of docking a rocket projectile in a tubular guide is to secure the projectile by the drive pins with a locking-docking device located on the launch tube, as, for example, in “Design of missile weapons. Design of multiple launch rocket systems." Edited by Dr. Tech. sciences, prof. ON THE. Makarovets. Tula State University Publishing House, 2011, p. 28-29) accepted by the authors as an analogue.

The projectile is fixed as follows. When loading, the projectile guide pin interacts with the locking-docking device. The device keeps the projectile from falling out during transportation and when pointing in a vertical plane, and also ensures that the projectile is held during launch until the thrust reaches the lock opening force.

However, when using projectiles with a rotating stabilizer and projectile extension over 25 calibers, fixation by means of guide pins does not provide the required reliability with significant overall and weight characteristics of the projectile.

Thus, the objective of this technical solution was to ensure the fixation of the projectile in the tubular guide.

The closest in technical essence to the rocket projectile proposed by the authors, launched from a tubular guide, is the “Roll-stabilized rocket projectile for launching from a tubular guide with a screw groove” according to RF patent No. 2726103, publ. 07/09/2020, BI No. 19 accepted by the authors as a prototype. It contains a control system unit located in front of the warhead, a rocket engine, a stabilizer unit with a contact block, drive pins, a fairing and a blade lock. When loading, the projectile is fixed to the body of the rocket part.

At the same time, this projectile does not provide reliable fixation in the tubular guide after loading and during combat operation.

The objective of the known technical solution is to increase the reliability of the functioning of the missile during loading and preparation for launch, to reduce the mass characteristics of the projectile and, as a result, to increase the range.

Common features with the technical solution proposed by the authors are the presence of a block of stabilizers, drive pins, a fairing and a blade retainer.

Unlike the prototype, in the proposed missile, launched from a tubular guide, the stabilizer block is equipped with a support with a stop with an inclination angle of 18°-20° to the cross-sectional plane of the projectile, in addition, the support is located at a distance of 0.005...0.02 caliber of the projectile from the axis pins, while the outer diameter of the support does not exceed the caliber of the projectile.

In particular cases, that is, in specific forms of execution, the missile is equipped with a rotating fairing on which a support with a base is mounted, and a longitudinal groove is made on the latch, placed coaxially with the support, while a sectoral groove is made at the base of the support or the support is formed on a block of stabilizers.

This allows us to conclude that there is a cause-and-effect relationship between the set of essential features of the proposed technical solution and the achieved technical result.

The indicated features, which are distinctive from the prototype and which are covered by the requested scope of legal protection, are sufficient in all cases.

The objective of the proposed invention is to ensure reliable fixation of a rocket projectile in a tubular guide after loading and during combat operation.

This technical result is achieved by the fact that, unlike the prototype, the stabilizer block is equipped with a support with a stop with an angle of inclination of 18°-20° to the cross-sectional plane, in addition, the support is located at a distance of 0.005...0.02 caliber of the projectile from the axis of the pins, while the outer the diameter of the support does not exceed the caliber of the projectile.

In particular cases, that is, in specific forms of execution, the missile is equipped with a rotating fairing on which a support with a base is mounted, and a longitudinal groove is made on the latch, placed coaxially with the support, while a sectoral groove is made at the base of the support or the support is formed on a block of stabilizers.

A new set of design elements, as well as the presence of connections between the essential features of the proposed missile, made it possible, in part, due to:

- supplying the stabilizer block with a support with a stop with an angle of inclination of 18°-20° to the cross-sectional plane of the projectile - will provide the required reliability when the stop interacts with the mating part located on the tubular guide of the combat vehicle. When the angle of inclination of the stop is greater than 20°, the required reliability of interaction between the stop and the mating part located on the tubular guide is not ensured, which can lead to spontaneous release of the projectile from the tubular guide. When the angle of inclination of the stops is less than 18°, the contact area of the stop with the mating part will be insufficient to prevent spontaneous release of the projectile at large elevation angles of the tubular guide;

- placing the support at a distance of 0.005...0.02 caliber of the projectile from the axis of the pins - will provide the ability to launch rockets from the standard guide without making any changes to the design of the guide;

- making the outer diameter of the support not exceed the caliber of the projectile - will ensure loading of various types of projectiles into the tubular guide;

The features that characterize the alleged invention in particular cases, that is, in specific forms of execution, allow, in part, due to:

- supplying the projectile with a rotating fairing on which a support with a base is mounted - to ensure the possibility of using the proposed technical solution on rockets with a rotating fairing;

- making a longitudinal groove on the latch, placed coaxially with the support - to ensure the joining of the support located on the rotating fairing with the mating part located on the tubular guide of the combat vehicle;

- execution of a sectoral groove at the base of the support - will ensure the prevention of spontaneous release of the projectile from the tubular guide after loading and during combat work;

- formation of a support on the stabilizer block - increase the reliability of the support by making it in the body of the centering thickening.

The essence of the invention is illustrated by drawings, where in Fig. 1 shows a general view of the rocket. In fig. Figure 2 shows a block of stabilizers with a support with a stop. In fig. Figure 3 shows a support with a sectoral groove.

The rocket contains a block of stabilizers 1, drive pins 2, a fairing 3 and a retainer 4 of the blades 5. On the block of stabilizers 1 there is a support 6 with a stop 7. The angle of inclination of the stop 7 is equal to α (18°-20°) to the cross-sectional plane of the projectile (B -IN). The support 6 is located at a distance a (0.005...0.02) of the projectile caliber D from the axis of the pins 2. The outer diameter d of the support 6 does not exceed the caliber of the projectile D.

In particular cases of execution, the projectile is equipped with a rotating fairing 1 on which the support 6 is mounted, and on the clamp 4 there is a longitudinal groove 8 made coaxially with the support 6. At the base 9 of the support 6 there is a sectoral groove 10. The support 6 is formed on the block of stabilizers 1.

The described missile works as follows.

During the loading process, the rocket with the lock 4 of the blades 5 is moved in the tubular guide 11. The driving pins 2, located on the block of stabilizers 1 with the fairing 3 and the base 9, provide a given position and the ability to rotate the projectile relative to the longitudinal axis. The stop 7 of the support 6 interacts with the mating part 12 of the tubular guide 11. The execution of the support 6 on the base 9 with a diameter d will ensure free loading into the tubular guide 11. Due to the coaxial placement of the groove 8 on the latch 4 with the support 6, the stop 7 of the support 6 freely interacts with mating part 12. The angle of inclination a of the stop 7 to the B-B plane ensures reliable fixation of the projectile in the tubular guide 11 after loading and during combat work. The sectoral groove 10 will ensure the prevention of spontaneous release of the projectile from the tubular guide after loading and during combat work. Placing the support 6 at a distance a will provide the ability to use a standard guide for launching various types of missiles without making any changes to the design of the guide.

In particular cases of execution, the formation of a support 6 on the block of stabilizers 1, for example, in a centering thickening, will ensure reliable fixation of the projectile in the tubular guide 11 of the previously created projectiles.

In particular cases of execution, the projectile is moved until the longitudinal groove 8 interacts with the mating part 12, located on the tubular guide 11. Due to the coaxial placement of the groove 8 on the latch 4 with the support 6, the stop 7 of the support 6 freely interacts with the mating part 12. Sectoral groove 10 ensures the prevention of spontaneous release of the projectile from the guide 11.

The formation of the support 6 on the stabilizer block 1 increases the reliability of the support, due to its implementation in the body of the centering thickening.

Making a missile launched from a tubular guide in accordance with the invention allows for reliable fixation of the missile in the tubular guide after loading and during combat operation.

This positive effect is confirmed by flight design tests of samples of missiles launched from a tubular guide, made in accordance with the proposed invention.

Currently, design documentation has been developed, and the entire range of tests of prototypes has been carried out.

Claims (2)

1. A missile launched from a tubular guide, containing a block of stabilizers with blades placed on it, drive pins, a fairing and a blade lock, characterized in that the missile is equipped with a rotating fairing of the stabilizer block, on which a support with a base and a stop having an angle is mounted an inclination of 18-20° to the cross-sectional plane of the projectile, in addition, the support is placed at a distance of 0.005-0.02 projectile caliber from the axis of the driving pins, while the outer diameter of the support does not exceed the caliber of the projectile. 2. The missile according to claim 1, characterized in that the latch has a longitudinal groove placed coaxially with the support, while a sectoral groove is made at the base of the support.

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