RU2764721C1 - Control system unit for a missile launched from a tubular guide - Google Patents

Abstract

FIELD: militarySUBSTANCE: invention relates to a control system for missiles of multiple rocket launcher systems. The control system unit of a missile launched from a tubular guide contains a body with an ogival part and aerodynamic rudders that open in flight, which are mounted on it, and consist of a base and a folding part. In this case, a shaft by means of a splined connection fastens the folding part and the base where the teeth are formed on the shaft, and the corresponding splines are in the front lug of the folding part and the base. In this case, the shaft is equipped with one or more flats and is installed with the ability to rotate and move longitudinally relative to the unfolding axis, under the action of a compression-torsion spring, in addition, a stop is made on each base lug.EFFECT: invention is aimed at ensuring reliable fixation and operation of aerodynamic rudders in the unfolded position during flight at supersonic speeds, as well as improving manufacturability.3 cl, 4 dwg

Description

The invention relates to a control system for multiple rocket launchers.

The object of the invention is a unit of the missile control system with increased firing accuracy, designed to control the projectile throughout the entire flight path.

Aerodynamic rudders are used as the most effective controls in multiple rocket launcher projectiles.

Thus, an aerodynamic steering wheel is known according to the patent of the Russian Federation No. 2535789, Bull. No. 35 publ. December 20, 2014, accepted by the authors as an analogue. It consists of a root part, a folding part, spring-loaded stoppers and a folding axle with a spring.

The opening of the rudders is as follows. When the rocket exits the container, the folding part of the rudder is no longer kept from turning by the inner surface of the transport and launch container, and under the action of a spring, the folding part turns around the axis of rotation and is fixed by means of a stopper.

However, when loading into a tubular guide, it becomes difficult to place them.

The closest in technical essence to the block of the control system of a rocket launched from a tubular guide proposed by the authors is the block of the control system according to the patent of the Russian Federation No. 2541552, BI No. 5, publ. February 20, 2015, adopted by the authors as a prototype. It contains a body with an ogival part and aerodynamic control surfaces mounted on it that open in flight, consisting of a base and a folding part.

Block control system of the prototype operates as follows. In the process of loading the projectile, the housing with the ogival part of the block is positioned coaxially with the tubular guide from the side of its breech and moved in the direction of the muzzle. Aerodynamic rudders due to placement on the ogival part do not prevent its free movement inside the tubular guide.

The objective of this technical solution was to ensure the loading and launch of guided projectiles from standard tubular guides designed to launch previously developed unguided and corrected projectiles of multiple launch rocket systems.

At the same time, this block of the control system does not provide reliable fixation of the rudders in flight.

Common features with the block of the control system of a rocket launched from a tubular guide, proposed by the authors, is the presence of a body with an ogival part and aerodynamic rudders mounted on it that unfold in flight, consisting of a base and unfolding parts.

Unlike the prototype, in the block of the control system proposed by the authors, the folding part and the base are fastened with a shaft by means of a spline connection, where the teeth are formed on the shaft, and the corresponding slots are in the front lug of the folding part and the base, while the shaft is equipped with one or more flats and is installed with the possibility of rotation and longitudinal movement relative to the unfolding axis, under the action of a compression-torsion spring, in addition, a stop is made on the ear of the base.

In special cases, that is, in specific forms of execution, the compression-torsion spring is fastened to a sleeve rigidly fixed on the shaft, the shaft is provided with a double-sided flat.

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

The indicated features, which are different 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 and operation of the aerodynamic rudders in the unfolded position during flight at supersonic speeds, as well as improving manufacturability.

A new set of design elements, expressed in the presence of nodes that are new in comparison with the prototype, the relative position of the nodes and the presence of connections between them allow, in part, due to:

- fastening the unfolding part and the base with a shaft by means of a spline connection, where the teeth are formed on the shaft, and the corresponding splines - in the front lug of the unfolding part and the base to ensure reliable fixation of the shaft with the unfolding part and the base;

- a shaft equipped with one or more flats and installed with the possibility of rotation and longitudinal movement relative to the unfolding axis to ensure the interaction of the shaft with the base;

- using a compression-torsion spring, rotate the shaft with the folding part at the same time and move it in the longitudinal direction so that the shaft teeth interact with the splines of the base.

- making a stop on the lug of the base to ensure the fixation of the folding part in a predetermined position when opening the aerodynamic rudders.

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

- fastening the compression-torsion spring with a sleeve rigidly fixed on the shaft, to ensure the reliability of the rudder folding mechanism by transferring the torque necessary to rotate the shaft with the folding part from the compression-torsion spring to the shaft;

- supplying the shaft with a double-sided flat to ensure reliable fixation of the unfolding part with the base of the aerodynamic steering wheel.

The essence of the invention lies in the fact that the control system unit contains a body with an ogive part and aerodynamic rudders mounted on it that open in flight, consisting of a base and a folding part, unlike the prototype, according to the invention, the folding part and the base are fastened with a shaft by means of a spline connection, where the teeth are formed on the shaft, and the corresponding slots are in the front lug of the unfolding part and the base, while the shaft is equipped with one or more flats and is installed with the possibility of rotation and longitudinal movement relative to the unfolding axis, under the action of a compression-torsion spring, in addition, on the base is formed stop, the compression-torsion spring is fastened with a sleeve rigidly fixed on the shaft, the shaft is equipped with a double-sided flat.

The essence of the invention is illustrated by drawings, where in Fig. 1 shows a general view of the control system unit, in Fig. 2 is a section of the rudder folding mechanism, in FIG. 3 - section of the spline connection of the shaft with the eye of the folding part, in Fig. 4 is a section of the rudder folding mechanism with the aerodynamic rudder of the control system unit opened.

The control system unit comprises a body 1 with an ogival part 2, aerodynamic rudders 3 that open in flight, consisting of a base 4 and a folding part 5. The folding part 5 and the base 4 are fastened by a shaft 6 by means of a spline connection, where the teeth 7 are formed on the shaft 6, and the splines 8 - in the front ear 9 of the folding part 5 and in the ear 10 of the base 4. The shaft 6 is equipped with one or more flats 11 corresponding to the groove 12 in the base 4 and is installed with the possibility of rotation and longitudinal movement relative to the unfolding axis 13, under the action of a compression-torsion spring 14. On the lug 10 of the base 4, a stop 15 is made. In special cases, the compression-torsion spring 14 is fastened to the sleeve 16, rigidly fixed on the shaft 6, the shaft 6 is equipped with a double-sided flat 11.

The described block of the control system of a rocket launched from a tubular guide operates as follows.

After the projectile leaves the guide, the steering wheel 3 of the control system unit releases the folding part 5. Under the action of the compression-torsion spring 14, the shaft 6 rotates the folding part 5 until it interacts with the stop 15, then the shaft 6 moves in the longitudinal direction along the axis 13, while the teeth 7 of the shaft 6 interact with splines 8 of the base 4, and the flats 11 of the shaft 6 are placed in the groove 12 of the base 4. Thus, reliable fixation and operation of the aerodynamic rudders in the unfolded position under flight conditions is ensured.

In particular cases of execution, a compression-torsion spring fastened to a sleeve rigidly fixed on the shaft, a shaft equipped with a double-sided flat, provide manufacturability and ease of manufacture and assembly.

The implementation of the control system unit of a rocket launched from a tubular guide, in accordance with the invention, made it possible to ensure reliable fixation and operation of the aerodynamic rudders in the unfolded form in flight conditions at supersonic speeds, as well as to ensure the launch of guided projectiles from standard tubular guides designed to launch the developed previously unguided and corrected multiple rocket launcher projectiles.

Claims (3)

1. The control system unit of a missile launched from a tubular guide, containing a body with an ogive part and mounted on it aerodynamic control surfaces that open in flight, consisting of a base and a folding part, characterized in that the folding part and the base are fastened by a shaft by means of a spline connection, where the teeth are formed on the shaft, and the corresponding splines are in the front lug of the unfolding part and the base, while the shaft is equipped with one or more flats and is mounted with the possibility of rotation and longitudinal movement relative to the unfolding axis, under the action of a compression-torsion spring, in addition, on each lug of the base focus has been made. 2. The missile control system unit according to claim 1, characterized in that the compression-torsion spring is fastened to a bushing rigidly fixed to the shaft. 3. The missile control system unit according to claim 1, characterized in that the shaft is provided with a double-sided flat.

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