RU2258896C1 - Guided missile in launching pack - Google Patents

Abstract

FIELD: armament.

SUBSTANCE: the guided missile in a transport-launching pack has control surfaces installed in the horizontal plane, booster and propulsion engines, stabilizer unit consisting of flexible cantilevers combined around the body, a flare installed in the plane passing through the axis of the pack and the longitudinal axis of the flare and shifted from the vertical plane of symmetry. The angles of displacement of the planes of installation of the flare and control surfaces from the vertical plane of symmetry on the side of the missile trailing edge assembly are within 50 to 70 degrees in the counter-clockwise direction, and within 30 to 60 degrees in the clockwise direction respectively. The flare mass makes up 0.0075 to 0.015 of the missile mass.

EFFECT: enhanced probability of introduction of the guided missile in the field of vision of the guided missile instrument in the initial leg of the flight.

9 dwg

Description

The invention relates to the field of armament, in particular to guided missiles (UR) launched at low initial speeds from transport launch containers (TPK).

Known guided missile 9M115 anti-tank missile system (ATGM), adopted as a prototype [1], which includes:

- TPK with a hook located in a vertical plane,

- UR, made by the aerodynamic scheme "Duck", with a single-channel control system, consisting of sequentially located blocks:

- control compartment with rudders located in the same plane;

- mid-flight engine (MD);

- warhead;

- stabilizer block with three elastic consoles folded around the body;

- starting engine.

The missile is equipped with a tracer mounted on one of the stabilizer consoles in a plane passing through the axis of the tracer and the longitudinal axis of the container, offset from the vertical plane of symmetry, and rudders mounted arbitrarily in the horizontal plane.

SD is launched from the TPK by the starting engine with an initial speed of 50 ÷ 70 m / s. After the stabilizer consoles are opened (t = 0.05 ÷ 0.07 s), the tracer is fixed at the end of one of the consoles. The marching engine is turned on after 0.10 ÷ 0.15 s after the exit of the SD from the TPK. This design of UR is characterized by the fact that:

- has a mass unbalance relative to the longitudinal axis both when moving along the TPK, and after exiting it;

- has a different value of the aerodynamic stabilizing moment in two mutually perpendicular planes: in the plane of the rudders and the plane perpendicular to it.

The mass imbalance is a consequence of the presence of a tracer, which when the SD moves along the TPK is at a distance (R _TPK - R _tracer ) from the SD axis, and when the SD leaves the TPK at a distance (L _console + K _SD ) from the SD axis. Here, R _TPK is the radius of TPK, R _tracer is the radius of installation of the tracer, L of the _console is the swing of the stabilizer console, R _SD is the radius of the SD at the mount of the stabilizer console.

The presence of mass unbalance leads to an increase in the dispersion of the SD in the initial portion of the flight due to the appearance of a systematic initial disturbance during the movement of the SD along the TPK and the creation of an additional thrust eccentricity after turning on the main engine.

In addition, the aerodynamic asymmetry of the SD glider, due to the arbitrary installation of the rudders in the horizontal plane, also leads to an increase in the dispersion of the SD in the initial part of the flight, because the degree of impact of the crosswind on the SD significantly depends on the angular position of the rudders at the moment the SD leaves the TPK, which, together with the mass unbalance, significantly reduces the likelihood of shooting in the field of view of the guidance device and, as a result, the effectiveness of the ATGM as a whole.

These shortcomings are especially noticeable when shooting with a portable launcher, the line of sight of which runs at an altitude of 0.7 ÷ 1.0 m above the ground, and the initial velocity of the SD is 30 ÷ 70 m / s.

The objective of the invention is to increase the likelihood of SD shooting in the field of view of the guidance device by reducing SD deviations relative to a given (optimal) path in the initial flight section by reducing the effect of mass unbalance and aerodynamic symmetry of the SD glider.

This is achieved by the fact that in a guided missile in a container containing rudders mounted in a horizontal plane, starting and marching engines, a stabilizer block consisting of elastic consoles folded around the body, one of which has a tracer mounted in a plane passing through the axis container and the longitudinal axis of the tracer and offset from the vertical plane of symmetry, the angles of displacement of the installation planes of the tracer and the rudders in the direction from the vertical plane of symmetry from the tail of the SD are in the range of 50–70 degrees in the counterclockwise direction and 30–60 degrees in the clockwise direction, respectively, while the mass of the tracer is 0.0075–0.015 mass of the SD.

The proposed technical solution allows to increase the likelihood of shooting in the field of view of the guidance device by reducing the dispersion of the guided missile in the initial portion of the flight and to reduce lateral deviations of SD from the influence of the side wind, while ensuring the shooting of SD in the field of vision of the guidance device at an initial speed of 20 ÷ 30 m /from.

Illustrations explaining the principle of operation of the proposed technical solution are shown in figure 1 ÷ 9.

Figure 1, 2, 3 shows the design diagram of the SD. In figure 4, 5, 6 SD in the TPK. Figure 7 shows the deviation value of SD (Z) at the entrance to the field of view of the guidance device, depending on the angular position of the tracer (γ) relative to the vertical plane of symmetry. On Fig shows the value of the lateral deviation of the SD (Z) from the influence of the crosswind (W _x ) with the angular position of the consoles of the rudders (γ) at the entrance of the SD in the field of view of the guidance device. Figure 9 shows the probability of shooting in the field of view of the guidance device, depending on the values of the deviation of the SD from a given flight path.

UR (figure 1, 2, 3) consists of sequentially located blocks:

- control compartment 1 with rudders 6;

- mid-flight engine 2;

- warhead 3;

- stabilizer block 4 with elastic consoles 7, on one of which tracer 8 is installed;

- coils of a wireline 5.

SD placed in TPK 9 (Figs. 4, 5, 6) is fixed in a predetermined position, determined by risks 10 and 10 ', applied to the bottom of the SD shell and on the surface of TPK in the region of the back cover, respectively. The elastic console (stabilizer) in the folded state together with the tracer is held by the screed 11, the steering wheel consoles 6 are mounted on the axis and are folded in the container on the side surface of the SD housing. TPK 9 is mounted on the PU using the hook 12 located in the vertical plane of symmetry with the axis of the TPK.

The position of the tracer in the TPK is determined by the angle between the vertical plane of symmetry and the plane passing through the axis of the container and the tracer.

After leaving the TPK, the flight of the SD takes place along a ballistic trajectory. By the beginning of control (t = 0.3 ÷ 0.5 s), the missile is shot in the field of view of the guidance device PU. The presence of an imbalance in the mass of the tracer creates eccentricity from the starting (in TPK) and marching engines (t on _ML = 0.08 ÷ 0.12 s), which, with an arbitrary orientation of the SD in the TPK, leads to a deviation both in course and pitch. The influence of the side wind on the deviation along the SD course with asymmetric aerodynamic characteristics (rudders in one plane) is especially significant.

It was experimentally established that the mass ratio of the tracer and the SD, ranging from 0.0075 to 0.015, in combination with the position of the SD in the TPK, in which the angle between the vertical plane of symmetry and the axis of the tracer is in the range from 50 to 70 degrees, and the angle between the vertical plane of symmetry and the axis of the rudders in the range from 30 to 60 degrees, provides the minimum deviation of the SD in the initial section of the flight from the calculated trajectory, the value of which does not exceed 0.2 m, the probability of shooting P is estimated at P = 0.94 ÷ 0.96.

Application of the proposed technical solution on small-sized SDs, having in their design a tracer and rudders in one plane, allows:

- increase the probability of shooting in the field of view of the guidance device;

- to increase the efficiency of the dynamics of flight of UR in the initial section;

- and, as a result, the effectiveness of the ATGM as a whole.

Sources of information

1. ATGM 9M115: Technical Description 9K115. - M .: Military publishing house of the Ministry of Defense of the USSR, 1978

Claims (1)

Guided missile in a transport and launch container, containing rudders, starting and cruising engines, a stabilizer block consisting of elastic consoles folded around the body, one of which has a tracer mounted in a plane passing through the axis of the container and the longitudinal axis of the tracer and offset from vertical plane of symmetry, characterized in that the angles of displacement of the planes of installation of the tracer and rudders from the vertical plane of symmetry from the tail of the rocket are in the range of 50 ÷ 70 degrees in eg occurrence counterclockwise and 30 ÷ 60 degrees in the clockwise direction, respectively, wherein the tracer is 0.0075 mass ÷ 0.015 rocket weight.

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