RU2309376C1 - Progectile - Google Patents

Abstract

FIELD: armament, in particular, projectiles and missiles.

SUBSTANCE: the projectile has a jet engine, blades made in the form of arches whose bases are fastened in hinge joints located in eyes. The hinge joint axles of each blade are aligned. An the process of flight the stabilizing force of the arch blades is produced by their surfaces.

EFFECT: enhanced stiffness of the blades at a decrease of action of cross wind on the projectile.

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Description

The present invention relates to the field of rocket technology and can be used in small-sized missile systems.

A known projectile launched from a launch tube having a stabilizer block containing blades expanding along the axis of the projectile, retracted into its body and pivotally mounted in its tail section. (ATGM Javelin USA, Collection of scientific and technical information No. 2 (12), pp. 46, 48).

The device is simple in design and reliable in operation, however, it has a drawback in the small area of the blades and their stiffness due to cantilever fastening, which for rotating shells with a jet engine can lead to a change in the rotational speed in flight. To increase the area of the blades, it is necessary to have free volume on board the projectile beneath them, which entails an increase in dimensions along the length and passive mass of the projectile.

The closest analogue (prototype) of the present invention is a projectile containing pivotally mounted on its tail of the blade, the axis of which are located across the longitudinal axis of the projectile. In the folded initial position before firing, the blades are located in the rear of the projectile and are shifted axially back in the receiver. After the shell leaves the barrel under pressure of the cumulative gases remaining in the cavity, the receiver moves from the tail of the shell to the limiter. At the same time, the blades, consisting of two sections, under the pressure of the spring due to their own beveled edges rotate along the guide surface of the receiver around the axes fixed to the receiver. In this case, the sections are telescopically extended and both sections of each blade under the influence of the oncoming flow occupy their working position (US Patent No. 6454205, publication of March 30, 2001, IPC 7 F42B 10/14).

The advantage of this design is to reduce the required free volume on the stern under the expandable blades. However, there are a number of disadvantages. Such a blade has a large projection area in the transverse direction, which leads to an increase in the impact of the side wind on the projectile. The mechanism has a large passive weight and structural complexity (due to the presence of springs of the extension device, guides), which can lead to failure in flight. The blade consists of two sections, which leads to an increase in its thickness, while the aerodynamic drag of the projectile increases, and stiffness and reliability decrease.

The objective of the present invention is to increase the stiffness of the blades while reducing the impact of side wind on the projectile.

To solve this problem, in a projectile containing blades pivotally mounted on its tail, the axes of which are transverse to the longitudinal axis of the projectile, the blades are made in the form of arches, the bases of which are fixed in hinges placed in the eyes, with the hinge axes of each blade aligned and the eyes of adjacent the blades are fixed on a common basis.

Due to the fact that the blade is made in the form of an arch and is equipped with two hinges, the stiffness of the blade increases significantly and the impact of side wind on the projectile is reduced due to the fact that in flight one of the sides of the arch stabilizer is in the aerodynamic shadow of the other.

The invention is illustrated in graphic materials. The figures depict:

Figure 1 - a projectile with a jet engine;

Figure 2 is an enlarged view of the stern of the engine with open blades;

Figure 3 is an enlarged front view of the aft engine with open blades;

Figure 4 - a projectile with a jet engine with folded blades.

The projectile consists of:

1 - marching stage, 2 - jet engine, 3 - arched blades, 4 - hinges, 5 - eyes, 6 - base, 7 - aft of the engine, 8, 9, 10 - surfaces of arched blades.

The device operates as follows.

When moving through the pipe of a projectile 1 with a jet engine 2, the arched blades 3, fixed in hinges 4 of the eyes 5 on the base 6 of the aft 7, are held in a folded position by its wall. When leaving the container, the blades 3, folded longitudinally along the axis of the projectile, are fully open by inertia and due to the aerodynamic resistance of the air or due to the energy of the springs giving a pushing impulse to the blades. During the flight, the stabilizing force of the arched blades is created by surfaces 8, 9 and 10. In this case, the influence of the side wind on one of the surfaces 8 and 9, due to the presence of one of them in the aerodynamic shadow of the other, is small.

Thus, the present invention allows:

- significantly increase the stiffness of the blades due to the implementation of the blades in the form of an arch, equipped with two hinges;

- reduce the impact of crosswind due to the fact that in flight one of the sides of the arched stabilizer is in the aerodynamic shadow of the other.

All this, ultimately, allows to increase the performance characteristics of the rocket.

Claims (1)

A projectile containing blades pivotally mounted on its tail end, the pivot axis of which are located across the longitudinal axis of the projectile, characterized in that the blades are made in the form of arches, the bases of which are fixed in hinges placed in the eyes, while the axis of the hinges of each blade are aligned, and the eyes adjacent blades are fixed on a common base.

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