RU2291381C1 - Guided missile (modifications) - Google Patents

Abstract

FIELD: armament.

SUBSTANCE: the guided missile, having a canard aerodynamic configuration, has a cylindrical body, stabilizer and aerodynamic control surfaces. A circular pylon made of a ring plate coupled to the body by plane-surface plates in installed on the body nose before the control surface. According to the other modification, a plane-surface pylon made of plates cantilever fastened an the body at an angle of 45 deg. relative to the plane of the control surface cantilevers is installed on the guided missile nose behind the control surface.

EFFECT: enhanced efficiency of the guided missile.

2 cl, 8 dwg

Description

The invention relates to rocket weapons, in particular to the field of small-sized guided missiles, and can be used in missile designs made according to the duck aerodynamic design.

Known anti-tank guided projectile, adopted for the prototype, consisting of a cylindrical body with a nose of a smaller diameter, a stabilizer, a rocket engine, aerodynamic controls - rudders mounted on the bow of the shell [ATGM 9M113. Technical description instruction manual. - M .: Military publishing house, 1974].

The disadvantage of the prototype is the low efficiency of the aerodynamic controls, the bearing capacity of which is limited due to the nonlinear nature of the dependence of the lifting force and the steering moment of the rudders on their deflection angles and projectile angles of attack. In addition, unsteady, tear-off flow around the blunt nose of the shell of the shell affects the decrease in the bearing characteristics (lift) of the rudders located on the bow of the hull.

The task of the invention is to increase the efficiency of projectile control by increasing the efficiency of aerodynamic controls.

The solution to the problem lies in the fact that in a guided projectile made according to the aerodynamic scheme "duck" containing a cylindrical body, a stabilizer and aerodynamic controls - steering wheels:

1. An annular pylon made of an annular plate connected to the casing by flat plates is installed on the bow of the hull in front of the steering wheel, while the ratio of the difference between the radii of the ring plate and the bow of the hull to the span of one console is 0.2 ÷ 0.4, the ratio of the ring chord the plate to the side chord of the steering wheel is 0.2 ÷ 0.5, and the ratio of the distance between the annular plate and the wheel to the side chord of the steering wheel is 0.1 ÷ 0.3;

2. On the bow of the hull behind the wheel there is a flat pylon made of plates cantilevered on the casing in a plane at an angle of 45 degrees relative to the plane of the steering consoles, while the ratio of the span of the pylon console to the span of the steering console is 0.5 ÷ 0.8, the ratio of the side chord of the pylon console to the side chord of the steering console is 0.3 ÷ 0.5, and the distance between the steering wheel and the pylon along the longitudinal axis of the projectile is 0.1 ÷ 0.5 of the length of the side chord of the steering wheel.

The use in the design of a guided projectile of an annular pylon on the bow of the hull in front of the steering wheel and a flat pylon behind the wheel in a plane at an angle of 45 degrees relative to the plane of the rudders can increase the efficiency of aerodynamic controls and, as a result, increase the dynamic characteristics of the projectile.

Illustrations explaining the principle of action of the proposed solution are shown in figures 1-8. In Fig.1, 2, 3 presents a sketch of a guided projectile with an annular pylon, Fig.4, 5, 6 - guided projectile with a flat pylon, Fig.7, 8 are graphs of the dependence of the coefficient of lift of the steering wheel (C _ur ) from the effective angle of attack (α _eff ) guided projectile with annular and flat pylons.

A guided projectile (Fig. 1 ÷ 6) consists of a housing 1, a stabilizer 2, aerodynamic controls 3, the bow of the housing 4, an annular pylon 5, a flat pylon 6. In Fig. 7: 1 is a curve of the dependence of the coefficient of lift of the steering wheel with _ur prototype, 2 - dependence curve C _ur = ƒ (α _eff ) steering wheel with an annular pylon. On Fig: 1 - the dependence of the coefficient of lift of the rudder with _ur prototype, 2 - dependence of C _ur = ƒ (α _eff ) rudder with a flat pylon.

The designations shown in figure 2, 5, characterize the parameters of the steering wheel, annular and flat pylons:

L _P , L _PP - the span of one console of the steering wheel and a flat pylon,

;

In _R , In _PP , In _KP - the onboard chord of the steering wheel, flat pylon and ring pylon, respectively

;

R _KP , R _N - the radius of the annular pylon and the bow of the hull, R _KP -R _N = ΔR _KP

ΔХ _KP - the distance between the annular pylon and the steering wheel,

ΔХ _ПП - the distance between the steering wheel and flat pylons,

With _y (Fig.7, 8) is the coefficient of lift, referred to the own area of the steering wheel;

α _eff - effective angle of attack, α _eff = K _α α + δ _p ,

where α is the angle of attack of the projectile, δ _p is the angle of deviation of the steering wheel. To _α - the interference coefficient of the housing on the steering wheel.

This design works as follows. In flight, a guided projectile when the steering wheel is rotated through an angle δ _{p is} deployed relative to the center of mass of the projectile at the angle of attack α. In this case, the steering consoles are at an angle α and δ _p , i.e. at an effective angle of attack α _eff = K _α α + δ _p . For anti-tank guided shells made according to the "duck" scheme, the range of flight angles of attack at angles of deviation of the rudder 13 ÷ 15 degrees is 4 ÷ 6 degrees. The effective angle α _eff is 18 ÷ 22 degrees.

For optimal steering characteristics of the aerodynamic characteristics of the prototype, the lifting force at such angles has a maximum value (Fig. 7 (1), 8 (1)). At angles α _eff > 20 °, the rudder lifting force does not increase at large angles around the steering consoles due to flow stall the rudder lift coefficient is nonlinear in terms of angles α and δ _p . The installation on the bow of the shell shell of the annular pylon according to paragraph 1 of the formula and the flat pylon according to paragraph 2 of the formula creates a smooth (without disruption) flow around the steering wheel to large angles of attack α = 10 ÷ 12 ° (α _eff = 25 ÷ 30 °). As a result of this, the control force and the moment of the steering wheel increase, and the available projectile overload increases. In addition to the positive impact of the pylons on the steering efficiency, annular and flat pylons additionally increase the lift of a guided projectile.

Testing various versions of the model of a projectile in wind tunnels, as well as flight tests of a guided projectile, made it possible to choose the optimal ratio: the span of the console of the flat pylon and rudder 0.5 ÷ 0.8, the side chords of the console of the flat pylon and rudder - 0.3 ÷ 0.5 , annular pylon and rudder 0.2 ÷ 0.5; the difference between the radii of the annular plate and the bow of the hull to the span of the steering console is 0.2 ÷ 0.4.

This design with optimal geometric parameters of the annular and flat pylons increases the available overload by 20 ÷ 40%, which allows to increase the range of the projectile, to increase accuracy when shooting at moving targets.

Under severe restrictions on the overall mass characteristics during the design of new samples, as well as the modernization of standard small-sized guided projectiles, it is possible to increase the control efficiency only by increasing the efficiency of the aerodynamic characteristics of the projectile glider controls.

Thus, the application of the proposed technical solution in small-sized guided missiles with subsonic and transonic glider speeds allows:

- to improve the aerodynamic quality of the airframe without increasing the overall mass characteristics of the guided projectile;

- to increase the accuracy of guidance of a guided projectile and, as a result, the effectiveness of the use of anti-tank guided complex as a whole.

Claims (2)

1. A guided projectile made according to the aerodynamic scheme "duck", containing a cylindrical body, stabilizer and aerodynamic controls - rudders, characterized in that on the bow of the body in front of the steering wheel there is an annular pylon made of an annular plate connected to the body by flat plates, the ratio of the difference between the radii of the annular plate and the bow of the body to the span of the steering console is 0.2 ÷ 0.4, the ratio of the chords of the annular plate to the side chord of the steering wheel is 0.2 ÷ 0.5, and the ratio of the distances I between the annular plate and the wheel to the vehicle steering chord is 0.1 ÷ 0.3. 2. A guided projectile made according to the aerodynamic scheme "duck", containing a cylindrical body, a stabilizer and aerodynamic controls - rudders, characterized in that on the bow of the steering wheel there is a flat pylon made of plates cantilevered on the body in a plane at an angle 45 ° relative to the plane of the steering consoles, while the ratio of the span of the pylon console to the span of the steering console is 0.5 ÷ 0.8, the ratio of the side chord of the pylon console to the side chord of the steering wheel is 0.3 ÷ 0.5, and the distance between the steering wheel and the pylon along the longitudinal axis of the projectile is 0.1 ÷ 0.5 of the length of the side chord of the steering wheel.

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