RU2234667C1 - Missile - Google Patents

Abstract

FIELD: rocketry; guided missiles with aerodynamic actuators.

SUBSTANCE: proposed missile is made according to standard aerodynamic configuration. It has body where engine, guidance equipment and control systems, fighting equipment, four fixed wings and four aerodynamic control surfaces are arranged. Wings and control surfaces are smoothly distributed relative to longitudinal axis of body.

EFFECT: enhanced maneuverability.

6 dwg

Description

The invention relates to rocket technology, in particular to guided missiles, and can be used in various types and classes of missiles with aerodynamic controls.

Known rocket made in the normal aerodynamic configuration, comprising a housing, an engine placed therein, guidance system and control systems equipment, combat equipment, as well as four fixed wings and four aerodynamic control wheels located on the housing uniformly with respect to its longitudinal axis.

This missile with varying degrees of disclosure is described in the book "Designing SAM" - M .: MAI, 1999, p.20 and the magazine "Technology and armament yesterday, today, tomorrow ..." No. 5-6, 1999, p.36. The last technical solution is taken as a prototype for this application.

This surface-to-air guided missile has a bicaliber cylindrical body and wings of small elongation with a trapezoidal shape in plan. The body and wings are the main elements that create lift. The bow has a lively shape.

In the solutions described above, the ratios of the geometric dimensions of the wing, rudder and rocket body are not presented, which does not allow us to judge the possible aerodynamic characteristics, in particular, the lift coefficient and available overloads.

The aim of the invention is the development of highly maneuverable, high-altitude missiles with high aerodynamic characteristics.

This goal is achieved by the fact that in a guided missile, made according to the normal aerodynamic scheme, comprising a housing, an engine placed therein, guidance and control system equipment, combat equipment, as well as four fixed wings and four aerodynamic control wheels located on the body evenly relative to its longitudinal axis, the wings, aerodynamic steering wheels of the control system and the body are made in such a way that they have the following size ratios:

where S _KR - wing area;

S _M - the area of the midship rocket;

- относительная площадь крыла;

- relative wing area;

- относительная площадь руля;

- relative rudder area;

S _Р - rudder area;

λ _КР - wing lengthening;

L is the wingspan;

L _p - the scope of the steering wheel;

λ _K - extension of the rocket body;

L _K is the length of the rocket;

D _ECV is the diameter of a circle whose area corresponds to the area of the rocket model.

When using the rocket according to the invention, it is possible to defeat air targets, including highly maneuverable fighters and attack aircraft, day and night, in simple and difficult weather conditions, from any direction (omnidirectionality) with active information (interference) and maneuverable countermeasures of the enemy. A missile is capable of hitting such specific targets as a cruise missile, an air-to-air missile, etc.

A missile with the stated size ratio solves the problem of placement on a launcher in conditions of tight overall limitations. The optimal range of parameters was found from numerous studies of rockets of various geometries in wind tunnels and was confirmed by flight test results.

A rocket with a given ratio of geometric dimensions provides high aerodynamic characteristics in the entire range of its application.

Thus, the maximum angle of attack is _αmax ≈ 30 °, the maximum permissible transverse overload is _nmax ≈ 30 units in both the passive and active sections of the trajectory due to the introduction of hardware limitations.

If you go beyond the specified ratios of the size of the missile to a large extent loses its maneuverability due to a sharp increase in the coefficient of resistance C _X and a significant decrease in the coefficient of normal force C _Y.

Thus, the choice of the ratio of the size of the rocket within the specified limits ensures its high maneuverability in the range of angles of attack α ≈ 0 ÷ 30 ° and numbers M ≈ 0.6 ÷ 4.5.

The invention is illustrated by drawings.

Figure 1 shows a General view of the proposed rocket; figure 2 is a front view of figure 1; figure 3 is a section aa in figure 1; figure 4 is a graphical representation of the dependence of the coefficient of normal force on the relative area of the wing; figure 5 is a graphical depiction of the dependence of the coefficient of normal force on the numbers M; Fig.6 is a graphical depiction of the dependence of the drag coefficient on the relative area of the wing.

The missile includes a housing 1, including a front fairing 2 lively shape. Inside the housing 1 is placed guidance system equipment and control systems, as well as a propulsion system (not shown in the drawings).

The missile is arranged according to the normal aerodynamic scheme, in accordance with which four wings 3 are located on the body 1 in its central part and four rudders 4 in its rear part. The wings 3 and 4 rudders are placed on the body 1 evenly relative to its longitudinal axis.

To optimize the aerodynamic characteristics of the rocket, the ratio of the dimensions of the body 1 of the rocket, its wings 3 and rudders 4, selected above.

Missiles with wings of small elongation, providing a small transverse dimension, are designed for maneuvering at large angles of attack. From the point of view of aerodynamics, such configurations have the following distinctive features: the presence of cross-links; high bearing properties at large angles of attack.

The choice of the ratio of the sizes of the rudders, wings and the rocket body as a whole within certain limits allows us to reduce or eliminate a number of technical problems (or parts of these problems).

Maneuvering at large angles of attack (α ≈ 30 °) allows for a high level of transverse overloads over the entire range of missile use.

As you know, the magnitude of the transverse overload is proportional to the magnitude of the normal rocket force, which is determined by the formula

Y = C _y q q S

where C _Y is the coefficient of normal rocket strength;

q - velocity head, kg / m ² ;

S - characteristic size, m ² .

The value of the flight range of the rocket is inversely proportional to the resistance force of the rocket, which is determined by the formula

X = C _X q q S,

where C _X is the rocket drag coefficient.

Figure 4-6 shows the dependence of C _y , C _X from the declared parameters of the rocket.

A missile with the stated size ratio provides the highest maneuverability with a minimum drag coefficient.

These parameters are determined as a result of systematic research in the wind tunnels of missiles of various geometries and are confirmed by the results of flight tests.

When going beyond the declared parameters, the missile to a large extent loses its maneuverability due to a sharp decrease in the coefficient of normal force and an increase in the coefficient of resistance.

Thus, a rocket with the stated size ratio provides high aerodynamic characteristics in the entire range of its application, the maximum allowable overload is n _Umax ≈ 30 units at angles of attack α ≈ 30 °.

Claims (1)

A rocket made according to the normal aerodynamic scheme, comprising a housing, an engine placed therein, guidance and control system equipment, combat equipment, as well as four fixed wings and four aerodynamic control wheels located on the housing uniformly with respect to its longitudinal axis, characterized in that the wings, aerodynamic steering wheels of the control system and the body are made in such a way that they have the following aspect ratios:

where S _KR - wing area; S _M - the area of the midship rocket;

- relative wing area;

- relative rudder area; S _p - the area of the steering wheel; λ _КР - wing lengthening; L _p - the scope of the steering wheel; L is the wingspan; λ _K — lengthening of the rocket body; L _K - the length of the rocket; D _ECV is the diameter of a circle whose area corresponds to the area of the midship rocket.

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