RU2645322C1 - Guided projectile - Google Patents

Abstract

FIELD: weapons.

SUBSTANCE: invention relates to the field of weapons, in particular to the field of small-sized guided projectiles, mainly with subsonic and transonic flight speeds, and can be used in constructions with various aerodynamic schemes. Guided projectile, designed in the aerodynamic scheme "duck", contains a cylindrical body and a head part with a fairing, a steering unit and aerodynamic controls. Aerodynamic controls are made of a steering wheel, the arms of which are installed on the side surface of the head part fairing, and pylons rigidly fixed to the body in front of the rudder arms in the same plane. Consoles of the steering wheel and pylons are made of flat plates with airborne chords, installed on the side surface at an angle of 5–15 degrees to the longitudinal axis of the missile. Steering wheel is made with a rotational spanwise angle along the leading edge – 0 degrees from the root chord to 0.30–0.40 of the swing of the steering wheel console, then with a sweep angle of 55–65 degrees to the full swing of the steering wheel console. Swing of the pylon console is made with a ratio of 0.30–0.40 swing of the steering wheel console. Pylon side chord is made with a ratio of 0.40–0.50 to the length of the side chord of the steering wheel, and the gap between the leading edge of the steering wheel and the rear side of the pylon is 0.05–0.15 of the length of the side chord of the steering wheel console.

EFFECT: invention increases the effectiveness of the projectile control, its dynamic and ballistic characteristics, increases the flying range of the projectiles.

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Description

The invention relates to the field of armament, in particular to guided projectiles mainly with subsonic and transonic flight speeds, and can be used in missile designs with various aerodynamic schemes, including with a duck configuration.

Known guided projectile [Patent for invention RU 2233423 (State Unitary Enterprise Design Bureau of Instrument Engineering) 09/10/2002], adopted as a prototype.

A guided projectile consists of a steering drive unit with rudders mounted on a conical fairing of the head of the shell body, the main engine, warhead, and the stabilizer block.

The disadvantage of the prototype is the low efficiency of the projectile control due to the imperfect design of the aerodynamic rudders. The bearing capabilities of the prototype rudders are limited due to the nonlinear nature of the dependence of the controlled force and rudder moment on the attack angles and rudder deflection angles. In addition, this design of the rudders mounted on the conical head of the projectile reduces the effectiveness of the lifting force of the rudder, leads to an increase in the spacing of the center of pressure of the rudder, to increase the hinge moments.

The objective of this technical proposal is to increase the efficiency of projectile control by increasing the efficiency of aerodynamic controls - rudders mounted on the fairing of the head of the hull.

The problem is achieved in that in a guided projectile made according to the aerodynamic scheme "duck" containing a cylindrical body, a head part with a cowl, a steering unit, aerodynamic controls are made of a steering wheel, the console of which is mounted on the side surface of the cowl head part, and pylons rigidly mounted on the body in front of the steering consoles in one plane. Consoles of the steering wheel and pylons are made of flat plates with side chords mounted on the side surface at an angle of 5 ... 15 degrees to the longitudinal axis of the projectile, while the steering wheel is made with a variable sweep angle of sweep along the leading edge - 0 degrees from the root chord to 0.30 ... 0.40 of the span of the steering console, then with a sweep angle of 55 ... 65 degrees to the full span of the steering console, the span of the pylon console is made with a ratio of 0.30 ... 0.40 of the span of the steering console, the side chord of the pylon is made with a ratio of 0.40 ... 0 , 50 to the length of the side chord of the steering wheel, and elichina gap between the front edge and the rear wheel strut is 0.05 ... 0.15 chord length sides steering console.

Compared with the prototype, in the presence of common design features and properties, a guided projectile of the proposed design of aerodynamic controls allows to increase control efficiency, increase the dynamic and ballistic characteristics of the projectile without increasing the overall mass characteristics of the guided projectile by increasing the basic aerodynamic characteristics (force, control torque ) at large angles of attack of the projectile.

The principle of operation of the proposed solution is illustrated in graphic materials.

The guided projectile of the proposed design, shown in FIG. 1, consists of a housing with an elliptical head part 1, a steering gear unit 2, a steering wheel 3, a pylon 4, a marching engine 5, a warhead 6, a stabilizer unit 7.

In FIG. 2 shows the design of the rudder and pylon mounted on the head of the hull with elliptical contours of the side surface.

The designations shown in FIG. 2, characterize the geometric parameters of the rudder and pylon, where:

L _p , L _p - the span of the console of the steering wheel and pylon;

In _p , In _p - side chord of the steering wheel and pylon;

χ _s.k. , χ _s.k. - sweep angle of the front and rear edges of the steering wheel;

ϕ _p - the angle of inclination of the steering chord of the steering wheel to the longitudinal axis of the projectile;

Δh is the clearance between the steering wheel and the pylon;

X _o.r. - the distance from the nose of the leading edge of the steering wheel to the axis of the steering wheel.

In FIG. Figures 3 and 4 show the dependences of the lifting force C _y ^α and the pressure center ΔX _{dp of the} aerodynamic controls on the effective angle of attack α _eff :

8, 10 - prototype;

9, 11 - the proposed design according to the claims.

The effective angle of attack is determined by the dependence α _eff = K _α ⋅α + δ _p ,

Where

δ _p is the deflection angle of the aerodynamic controls;

α is the angle of attack of the guided projectile;

K _α - coefficient of influence of the body on the steering wheel.

For guided shells made according to the “duck” scheme, with subsonic, transonic flight speeds (Max = 0.5 ... 0.9) with rudders of the prototype, the range of flight angles of attack is α = 2 ... 3 ° with δ _p = 12 ... 13 °, α _eff = 15 ... 18 °.

For guided projectiles with rudders of the proposed design of the claims, α = 4 ... 6 °, δ _p = 15 ... 16 °, α _eff = 22 ... 24 °.

The increased efficiency of the rudders in the proposed solution is achieved by obtaining a linear dependence of the coefficient of lift of the rudders to large angles α and δ _p .

As a result of this, due to an increase in the lifting force of the rudders, an increase in the angle of attack of the projectile, the available overload increases, and the range of the projectile increases. In addition, this design of the steering wheel by reducing the spacing of the center of pressure at the same flight speeds with a guided projectile prototype has a lower value of articulated loads, which allows to reduce the overall mass characteristics of the steering gear.

So, the implementation of aerodynamic controls according to the claims installed on the head of the hull with elliptical (conical) contours, increases the efficiency of projectile control.

Conducted laboratory and flight tests of a guided projectile made it possible to choose the optimal geometric parameters of the aerodynamic controls - rudders mounted on an elliptical (conical) head part of the shell.

The use of this technical proposal in the construction of anti-tank shells made it possible to increase the effectiveness of projectile control, increase dynamic and ballistic characteristics, and increase the range of flight of shells of anti-tank systems.

Claims (1)

Guided projectile made according to the aerodynamic scheme "duck", containing a cylindrical body, a head part with a fairing, a steering gear unit and aerodynamic controls, characterized in that the aerodynamic controls are made of a steering wheel, the console of which is mounted on the side surface of the fairing of the head part, and pylons rigidly mounted on the housing in front of the steering consoles in one plane, the steering consoles and pylons are made of flat plates with side chords mounted on the side surface An angle of 5-15 degrees to the longitudinal axis of the projectile, while the steering wheel is made with a sweep angle varying in sweep along the leading edge - 0 degrees from the root chord to 0.30-0.40 of the span of the steering console, then with a sweep angle of 55-65 degrees to the full extent of the steering console, while the span of the pylon console is made with a ratio of 0.30-0.40 the span of the steering console, the side chord of the pylon is made with a ratio of 0.40-0.50 to the length of the side chord of the steering wheel, and the gap between the leading edge rudder and rear pylon is 0.05-0.15 the length of the side chord of the console console I am.

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