RU2616310C1 - Guided missile fin - Google Patents

Abstract

FIELD: weapons and ammunition.

SUBSTANCE: stabiliser comprises stacked on the surface of the missile body hollow blades. These blades are made of elastic plates held together by curvilinear edges. At the ends of the blades, the protrusions are made as cylindrical contact surfaces while being tubular guide missiles in its walls. The end surfaces of the projections are rounded. A blade projection from the blade tip until it is bent relative to the longitudinal plane in the direction of folding. The dimensions of the cylindrical projection and the angle of bending the blade determined by analytical relations.

EFFECT: increased reliability and security guided missile by reducing fluctuations of the missile in the initial part of the inner walls of exclusion and damage the guide at its assembly and operation by eliminating contact with the edges of the stabiliser of the tubular guide.

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Description

The present invention relates to the field of weapons, in particular to the design of small guided missiles fired from a tubular guide (container), and can be used in structures with various aerodynamic schemes.

Known stabilizer guided missiles launched from a tubular guide (container) (US patent No. 3103886 from 09/17/1963), adopted for the analogue containing hollow blades folding along the surface of the rocket body made of curved elastic plates connected by rectilinear edges and forming rigid hollow construction in open form.

Known stabilizer guided missiles launched from a tubular guide (container) (patent RU 2396508 C1), adopted as a prototype containing folding on the surface of the rocket body hollow blades made of elastic plates connected by edges, the elastic plate of the blade is bent in the form of a segment of a cylindrical surface, and the bonded edges of the plates are made curved according to a segment of the cylindrical surface.

The disadvantage of the analogue is that in this design, when the rocket is in the tubular guide (container), the sharp edges of the stabilizer blades are in direct contact with the walls of the container.

In the prototype, in comparison with the analogue, the stabilizer blades are made in the form of a surface with a single curvature in the form of a fragment of a cylindrical surface of elastic curved curved plates with a fastened curved edge. Due to the surface with a single curvature, which is preserved when the plates are connected to each other, when the blades are folded together, there are no irregularities (folds) at the ends of the plates and the stabilizer blades more accurately bend around the rocket body and exert less pressure on the container walls in comparison with the analogue, which reduces the initial disturbances due to lower pressure of the blades on the walls of the container. However, the design of the prototype, as well as the analogue, does not exclude the contact of the sharp edges of the stabilizer blades with the walls of the tubular guide. As a result, when fired, during the movement of the rocket along the container, the sharp edges of the stabilizers can crash into its walls and create additional forces that prevent the product from leaving the guide, which can lead to an increase in the initial perturbations of the rocket. The presence of initial disturbances leads to strong rocket vibrations in the initial portion of the flight. Such fluctuations can lead to the missile leaving the control field with its further fall or miss on the target, which reduces the effectiveness of the combat use of the rocket and the complex.

In addition, during the installation of the rocket in the container, as well as during the movement of the rocket in the container (due to gaps) during its transportation, the sharp edges of the stabilizer can damage the inner walls of the container, which can lead to a decrease in its strength and, consequently, to a decrease in reliability and safety products in general.

The task of the invention is to prevent contact of the edges of the stabilizer blades with the wall of the tubular guide (container).

The technical result of the invention is to increase the reliability and safety of a guided missile by reducing rocket vibrations in the initial section and eliminating damage to the inner walls of the container during its assembly and operation.

The problem is solved due to the fact that in the stabilizer of a guided missile launched from a tubular guide containing hollow blades folding along the surface of the rocket body made of elastic plates interconnected by curved edges, protrusions in the form of cylindrical are made (stamped) surfaces in contact while the rocket is in the tubular guide with its walls, and the end surfaces of the protrusions are rounded, and the blade section from the protrusion to the end of the blade is bent relative to its longitudinal plane in the folding direction.

Since the edges of the blade are made curved, the cylindrical surface of the protrusions made at a distance from the end of the blade on its chord having a length of? sufficient to accommodate the protrusion. To exclude the contact of the end of the blade with the wall of the tubular guide, the end portion of the blade in the free state behind the cylindrical protrusion is bent at an angle of 25 ... 30 degrees in the direction of folding of the blade.

The bending of the edges at the ends of the stabilizer blades by an angle of 25 ... 30 degrees allows them to be excluded from contact with the container wall during rocket rotation, and the presence of a cylindrical protrusion with rounded end surfaces prevents contact between the edges and the container wall during longitudinal (axial) rocket movements.

To obtain the smallest possible dimensions of the protrusion while maintaining the effectiveness of the technical solution, the radius of the cylindrical surface of the protrusion is chosen equal to 2 ... 8 thickness of the blade plate, the stamping height is from 0.3 to 1 radius of the cylindrical surface of the protrusion, and the stamping length, including end fillets, is at least 0, 3 lengths of the chord of the blade passing through the middle of the protrusion.

Moreover, the small length of the section of the limb of the edge of the blade, which is an insignificant part of its span, does not affect the aerodynamic characteristics of the rocket and does not reduce the strength characteristics of the blade, since the bend passes at the point of bonding of the edges. The length of the stamped protrusion, exceeding 0.3 of the length of the chord of the blade passing through the middle of the protrusion, allows to minimize the shoulder from the protrusion to the edges of the blade and to exclude their contact with the container wall under the action of bending moments that occur during transportation and firing of the rocket.

The invention is illustrated by graphic material (Fig. 1, 2, 3).

In FIG. 1, 2 shows the blade of the proposed stabilizer, consisting of two elastic plates 1 and 2 of thickness δ, interconnected by edges. The edge of the blade bent at an angle α? equal to 25 ... 30 degrees, and on the elastic plate 1 of the blade along a length l, a cylindrical protrusion 3 of radius R is stamped with rounded end surfaces of radius r.

In FIG. 3 shows a stabilizer of a guided missile mounted in a tubular guide 4. The proposed stabilizer is located in the rear of the missile and is a flexible blade 5, mounted on a cylindrical housing of the stabilizer.

This design works as follows. Before installing the rocket in the container, the blades are folded. During the folding of the stabilizer blades, curved elastic plates are compressed in the direction of each other under the action of an external force, as a result of which the structural rigidity decreases and an elastic surface forms, which, under the influence of an external force, is pressed against the rocket body, repeating its shape (enveloping it), and held in this position the walls of the container. The blades 5 are in contact with the wall of the container 4 with cylindrical protrusions 3, due to which, as well as bending the edges of the blades at an angle of 25 ... 30 degrees, contact of the edges of the 6 blades with the wall of the container is excluded. When transporting a rocket under the influence of overloads, its movement can occur (due to the existing gaps of the retention mechanism) along the container in the axial direction and along the roll. But due to the lack of contact between the edges of the stabilizer and the tubular guide during these movements, damage to the container does not occur. When installing a rocket in a container and moving it around the container during a shot, the contact of the stabilizer blades with the tubular guide passes along the protrusions 3, which have no sharp edges and do not cut into the walls of the container, providing minimal resistance and eliminating rocket disturbances in the initial flight phase due to increased friction forces of the stabilizer blades in the container.

Thus, the present invention improves the reliability and safety of a guided missile by reducing rocket oscillations in the initial section and eliminating damage to the inner walls of the container during its assembly and operation due to the exclusion of contact between the edges of the stabilizer and the tubular guide.

Claims (11)

A stabilizer of a guided missile launched from a tubular guide containing hollow blades folded over the surface of the missile body made of elastic plates fastened by curved edges, characterized in that at the ends of the blades protrusions are made in the form of cylindrical surfaces in contact with the missile in the tubular guide its walls, and the end surfaces of the protrusions are rounded, and the portion of the blade from the protrusion to the end of the blade is bent relative to its longitudinal plane folding direction, the dimensions of the cylindrical projection and the bending angle of the blade are defined by the relations               R = (2 ... 8) δ;               H = (0.3 ... 1) R;               l ≥ 0.3b;               α = 25 ° ... 30 °, where R is the radius of the protrusion of the blade, mm; h is the height of the protrusion of the blade, mm; l is the length of the protrusion of the blade, mm; δ is the blade plate thickness, mm; b is the length of the chord of the blade passing through the middle of the protrusion, mm; α is the angle of limb of the edge of the blade, degrees.

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