RU2259536C1 - Aircraft guided missile - Google Patents

Abstract

FIELD: armament.

SUBSTANCE: the missile has a body, homing head, control equipment system with four control actuators, power supply system, fighting equipment, replaceable engine installation, four fixed wings, four control surfaces and four destabilizers. The control surfaces and the destabilizers of the missile are made according to definite relations of dimensions.

EFFECT: when the innovation is used, reversal of the control moment is eliminated.

6 cl, 6 dwg

Description

The invention relates to the field of rocket technology, in particular to guided missiles, and can be used in various types and classes of missiles with a cross-shaped arrangement of aerodynamic surfaces.

Known air-to-air guided missiles belonging to one family of missiles, which are made according to the aerodynamic scheme "duck", contain a housing, a homing head located therein, control system equipment with four steering drives, an energy supply system, combat equipment, consisting of a non-contact fuse and a warhead, and a propulsion system, as well as four fixed wings, four control aerodynamic wheels, located on the body in tandem and symmetrically relative to its longitudinal axis and four fixed destabilizers mounted in front of the handlebars. These missiles with varying degrees of disclosure are described in the sources:

- A.V. Karpenko. Russian missile weapons 1943-1993, reference book, second edition, St. Petersburg, "PIKA", 1993, pp. 135, 145, 146,

- Russian Air Defense Aviation and Scientific and Technical Progress: Combat Systems and Systems Yesterday, Today, Tomorrow / Ed. E.A. Fedosova, M., Bustard, 2001, p. 214, 215, 282, 286-290.

This technical solution is most fully described in the last source. It is taken as a prototype for this application.

Missiles of this family have the same control system equipment with four steering gears, an energy supply system, combat equipment, rudders and wings. They have interchangeable, interchangeable homing heads - radar (semi-active or passive) and infrared (passive) and two interchangeable, interchangeable propulsion systems, differing in weight and dimensions. The homing heads, depending on their type, have either a parabolic nose, which is a body of revolution with a parabola forming in the form of a segment, (radar), or a parabolic nose with a blunt nose in the form of a hemispherical surface with a radius of 0.6 ... 0.7 from body radius (infrared). The missiles have four front fixed destabilizers located on the homing head, four control aerodynamic steering wheels located on the control system compartment, and four fixed wings located on the propulsion system.

A feature of the aerodynamic design of these missiles is the use of rudders, which have a large scope, a variable sweep along the leading edge and a narrowed root part.

It should be noted that replacing the homing head with a head of a different type in the general case entails a change in the aerodynamic parameters of the rocket, which makes it difficult to control.

The descriptions given in the sources mentioned above do not present the ratio of the geometric dimensions of the bearing and control surfaces and their relative location, which does not allow one to judge the possibility of ensuring the same and high aerodynamic parameters, including the balancing characteristics of missiles of this family when using interchangeable homing heads and propulsion systems that differ in weight and size.

When creating the invention, the task was to develop a family of missiles having interchangeable, interchangeable homing heads and propulsion compartments, and at the same time ensure the use of the same wings, rudders, steering drives and control system settings for all possible layout options.

As a technical result achieved by using the claimed invention, it should be noted on:

- elimination of the roll moment reversal inherent in missiles made according to the “duck” scheme due to the use of rudders of the described configuration with the claimed size ratios, which allows using the same rudders kinematically not interconnected to control and stabilize the rocket as relative to the lateral axes of the associated coordinate system, and relative to its longitudinal axis, and, thereby, eliminates the need to use to stabilize the rocket relative to its longitudinal axis located on the wings x control surfaces such as ailerons and their drives located in the engine compartment, which is undesirable when using interchangeable propulsion systems having a large difference in diameters,

- the possibility of obtaining due to the use of destabilizers with the claimed ratios of sizes close balancing values of the angle of attack α _{ball of the} rocket and the coefficient of normal force C _y in both longitudinal control channels, regardless of the shape, size and weight of the homing head,

- the ability to control the rudders of a large area through the use of hydraulic steering gears powered by a pump-battery system.

To solve the problem in a guided missile, carried out according to the aerodynamic scheme "duck", comprising a housing, a replaceable homing head placed therein, control system equipment with four steering drives having independent control, an energy supply system, combat equipment, a replaceable propulsion system, and four fixed wings located on the body in tandem and symmetrical with respect to its longitudinal axis, four aerodynamic steering wheels kinematically decoupled between each other with individual s rotation, having a large scale, the sign variable sweep on the leading edge and a tapered root portion and four fixed destabilizer established before rudders and hydroplanes destabilisers are designed in such a way that the following relations sizes:

χ _core = -20 ...- 15;

χ _con = 75 ... 80;

- относительная площадь двух консолей руля,Where:

- the relative area of the two steering consoles,

S _2p - the area of the two consoles of the rudders, m ² ,

S _m - mid-sectional section of the hull, m ² ,

λ _p - lengthening of the rudders,

l _p - the span of the steering wheel console, m,

- относительный размах консоли руля, м,

- relative span of the steering wheel console, m,

l _cr - the span of the wing console, m,

χ _core - sweep angle along the leading edge of the root part of the steering wheel, degrees,

χ _con - sweep angle along the leading edge of the end part of the steering wheel, degrees,

æ - narrowing of the root part of the steering wheel,

b _core - the size of the root chord of the steering wheel, m,

b _max ^{- the} size of the steering chord at the point of change of the sign of sweep of the leading edge, m,

- относительная площадь двух консолей дестабилизаторов,

- the relative area of the two console destabilizers,

S _2det - the area of two consoles of destabilizers, m ² ,

λ _dest - elongation of destabilizers,

l _dest - the span of the console of one destabilizer, m.

In this rocket, the steering gears are made hydraulic with power from the pump-storage system.

In the case of using a homing radar head with a parabolic bow at the position of the center of gravity of the rocket

^*)

^*)

( ^*) Hereinafter, dimensionless length parameters are given in fractions of the housing length of the corresponding variant.)

the location of the destabilizers on the rocket body is determined by the following relation

- положение центра масс ракеты в долях длины ее корпуса,Where:

- the position of the center of mass of the rocket in fractions of the length of its body,

X _t - the distance from the tip of the rocket to its center of mass, m,

L _corp - rocket body length, m,

- относительное расстояние между геометрическим центром площади дестабилизатора в плане и центром масс ракеты,

- the relative distance between the geometric center of the area of the destabilizer in plan and the center of mass of the rocket,

L _dest - the distance between the geometric center of the area of the destabilizer in the plan and the center of mass of the rocket, m

In the case of using an infrared homing head with a parabolic nose, having a blunted nose in the form of a hemispherical surface with a radius of 0.6 ... 0.7 from the radius of the body, with the center of gravity of the rocket

the location of the destabilizers on the rocket body is determined by the following relation

- положение центра масс ракеты в долях длины ее корпуса,Where:

- the position of the center of mass of the rocket in fractions of the length of its body,

X _t - the distance from the tip of the rocket to its center of mass, m,

L _corp - rocket body length, m,

- относительное расстояние между геометрическим центром площади дестабилизатора в плане и центром масс ракеты,

- the relative distance between the geometric center of the area of the destabilizer in plan and the center of mass of the rocket,

L _dest - the distance between the geometric center of the area of the destabilizer in the plan and the center of mass of the rocket, m

In the case of using a propulsion system with a diameter equal to 1.0 ... 1.1 of the diameter of the body, the following size ratios are implemented:

- отношение полных размахов рулей и крыльев,Where:

- the ratio of the full span of the rudders and wings,

L _pp - full range of rudders, m,

L _{p, cr} - full wingspan, m,

- относительное расстояние между осью вращения руля и носком бортовой хорды крыла,

- the relative distance between the axis of rotation of the steering wheel and the tip of the side chord of the wing,

l _cr - the distance from the nose of the rocket to the nose of the side chord of the wing, m,

l _ovr - the distance from the tip of the rocket to the axis of rotation of the steering wheel, m,

L _corp - rocket body length, m

In the case of using a propulsion system with a diameter equal to 1.1 ... 1.3 of the diameter of the body, the following size ratios are implemented:

- отношение полных размахов рулей и крыльев,Where:

- the ratio of the full span of the rudders and wings,

L _pp - full range of rudders, m,

L _{p, cr} - full wingspan, m,

- относительное расстояние между осью вращения руля и носком бортовой хорды крыла,

- the relative distance between the axis of rotation of the steering wheel and the tip of the side chord of the wing,

L _cr - the distance from the nose of the rocket to the nose of the side chord of the wing, m,

L _ovr - the distance from the tip of the rocket to the axis of rotation of the steering wheel, m,

L _corp - rocket body length, m

The selected geometry of the rudders and the ratio of their sizes to each other and with the dimensions of the wings and the hull ensure the elimination of the reverse of the control moment of the heel arising due to the bevel of the flow from the rudders to the wings, while the use of rudders kinematically not interconnected allows them to be controlled and rocket stabilization both relative to the lateral axes of the associated coordinate system, and relative to its longitudinal axis.

The selected ratios of the geometric dimensions of the destabilizers, rudders and the hull and their relative position provide, on the one hand, aerodynamic characteristics that are independent of the shape of the nose of the rocket, and, on the other hand, a significant improvement in the flow around the rudders due to their large scope and more stable behavior of the center pressure due to the use of rudders with reverse sweep. The independence of the aerodynamic characteristics of the shape of the nose of the rocket allows you to use for all possible layout options a control system with the same settings.

The use of hydraulic steering gears powered by a pump-accumulator system provides control over large rudders over the entire range of required rudder deflection angles and high-speed pressure with maximum rudder hinge values of 17 kgm.

The geometry of the rudders and destabilizers is determined based on the conditions for ensuring high maneuverability and reliable controllability of the rocket along all three channels. The ranges of geometric parameters proposed according to the invention are obtained from practical experimental studies in wind tunnels and are confirmed by flight test data. A missile with the indicated ratios of geometric dimensions provides the required maneuverable characteristics in the entire range of its application.

The invention is illustrated graphic materials, where:

figure 1 shows a General view of a rocket with a propulsion system with a small diameter and with interchangeable homing heads,

figure 2 shows a General view of a rocket with a propulsion system with an increased diameter and with interchangeable homing heads,

figure 3 shows a view of the steering wheels in plan,

figure 4 shows a view of the destabilizers in terms of

figure 5 shows graphs of the dependences on the angle of attack α coefficient η equal to the relative roll moment (referred to the moment of roll with the angle of attack equal to zero),

figure 6 shows graphs of the dependencies of the maximum balancing angle of attack α _ball from dimensionless parameters of destabilizers

The missile according to the invention comprises a housing 1. Inside the housing 1 there is a control system equipment 2 with four steering gears 3, which are independently controlled, an energy supply system 4 and combat equipment consisting of a non-contact fuse 5 and a warhead 6. The missile has interchangeable homing heads - radar 7 with a parabolic nose or infrared 8 with a parabolic nose having a blunted nose in the form of a hemispherical surface with a radius of 0.6 ... 0.7 from the radius of the housing 1. The missile has interchangeable doors gaming installations - a propulsion system 9 with a diameter equal to 1.0 ... 1.1 of the diameter of the housing 1, (Fig. 1) and a propulsion system 10 with a diameter equal to 1.1 ... 1.3 of the diameter of the housing 1, ( figure 2). The rocket has aerodynamic surfaces located on the body 1 in tandem and symmetrically with respect to its longitudinal axis and is made according to the duck aerodynamic scheme, according to which four aerodynamic rudders 11 are placed on the body 1 in front of four fixed wings 12. The rocket is equipped with four destabilizers 13 installed in front of the rudders 11, which are kinematically uncoupled among themselves, have individual rotation axes 14, large span, variable sweep along the leading edge and narrowed root hour t (Fig. 3). Destabilizers 13 are made in the form of trapezoidal plates in the plan (figure 4). The steering gears 3 are made hydraulic with power from the pump-storage system.

λ_р обеспечивается не только устранение реверса управляющего момента крена, т.е. сохранение положительного отношения

где М_{х упр} - момент крена, реализуемый изолированными рулями, М_{х фак} - фактически реализуемый момент крена с учетом эффекта влияния крыльев, во всем используемом диапазоне углов атаки (α≤40 град) и чисел Маха (0,6≤М≤5,0), но и удерживается в заданных пределах значение отношения момента крена при угле атаки, не равном нулю, к моменту крена при угле атаки, равном нулю (коэффициента

Критерием приемлемой эффективности рулей в канале крена является возможность реализации во всем используемом диапазоне углов атаки и чисел Маха значения η≥0,7. Типовое поведение зависимостей η(α) при дозвуковой (М=0,8) и сверхзвуковой (М=3,0) скоростях приведены на фиг.5.In the selected ranges for changing rudder parameters

λ _p provides not only the elimination of the reverse control moment of the roll, i.e. maintaining a positive attitude

where M _{x yr} is the heeling moment realized by the isolated rudders, M _{x fact} is the actual heeling moment taking into account the influence of the wings, over the entire range of angles of attack (α≤40 deg) and Mach numbers (0.6≤M≤5, 0), but the value of the ratio of the angular momentum at an angle of attack not equal to zero is also kept within the given limits by the angular momentum at an angle of attack equal to zero (coefficient

The criterion of acceptable rudder efficiency in the roll channel is the possibility of realizing the value η≥0.7 in the entire range of attack angles and Mach numbers used. The typical behavior of the dependences η (α) at subsonic (M = 0.8) and supersonic (M = 3.0) speeds is shown in Fig. 5.

и дестабилизирующим моментом

, позволяет сохранить в жестких пределах запас статической устойчивости при больших значениях балансировочного угла атаки (до 40 град) во всем диапазоне чисел Маха. Поведение максимального балансировочного угла атаки α_бал в зависимости от безразмерного параметра дестабилизаторов

показано на фиг.6.The use of destabilizers, which are characterized by a small elongation λ _dest <0.6, relative area

and destabilizing moment

, allows you to maintain a strict margin of static stability with large values of the balancing angle of attack (up to 40 degrees) in the entire range of Mach numbers. The behavior of the maximum balancing angle of attack α _ball depending on the dimensionless parameter of the destabilizers

shown in Fig.6.

Claims (6)

1. The missile, made according to the aerodynamic scheme "duck", comprising a housing, a replaceable homing head housed therein, control system equipment with four steering drives having independent control, an energy supply system, combat equipment, interchangeable propulsion system, and also located in tandem housing and symmetrically with respect to its longitudinal axis, four fixed wings, four kinematically decoupled aerodynamic rudders with individual rotation axes having a large swing, hydrochloric sign sweep on the leading edge and a tapered root portion and four fixed destabilizer established before rudders, which destabilize the handlebars and are designed in such a way that the following relations sizes:

χ _core = -20 ...- 15; χ _con = 75 ... 80;

Where

- the relative area of the two steering consoles; S _2p - the area of the two consoles of the rudders, m ² ; S _m - mid-sectional section of the hull, m ² ; λ _p - lengthening of the rudders; 1 _p is the span of the steering wheel console, m;

- relative span of the steering wheel console, m; 1 _cr - the span of the wing console, m; χ _core - sweep angle along the leading edge of the root part of the steering wheel, degrees; χ _con - sweep angle along the leading edge of the end part of the steering wheel, degrees; æ - narrowing of the root part of the steering wheel; b _core - the size of the root chord of the steering wheel, m; b _max - the size of the steering chord at the point of change of the sign of sweep of the leading edge, m;

- the relative area of the two console destabilizers; S ₂ dest _{- the} area of two consoles of destabilizers, m ² ; λ _dest - lengthening of destabilizers; 1 _dest - the span of the console of one destabilizer, m. 2. The rocket according to claim 1, containing a radar homing head with a parabolic bow, in which, with the center of gravity of the rocket

the location of the destabilizers on the housing is determined by the following relation

Where

- the position of the center of mass of the rocket in fractions of the length of its body; X _t - the distance from the tip of the rocket to its center of mass, m; L _corp - rocket body length, m;

- the relative distance between the geometric center of the area of the destabilizer in plan and the center of mass of the rocket; L _dest - the distance between the geometric center of the area of the destabilizer in the plan and the center of mass of the rocket, m 3. The rocket according to claim 1, containing an infrared homing head with a parabolic nose, having a blunted nose in the form of a hemispherical surface with a radius of 0.6 ... 0.7 from the radius of the hull, which, with the center of gravity of the rocket

the location of the destabilizers on the housing is determined by the following relation

Where

- the position of the center of mass of the rocket in fractions of the length of its body; X _t - the distance from the tip of the rocket to its center of mass, m; L _corp - rocket body length, m;

- the relative distance between the geometric center of the area of the destabilizer in plan and the center of mass of the rocket; L _dest - the distance between the geometric center of the area of the destabilizer in the plan and the center of mass of the rocket, m 4. The rocket according to claim 1, containing a propulsion system with a diameter equal to 1.0 ... 1.1 of the diameter of the hull, which has the following size ratios:

Where

- the ratio of the full span of the rudders and wings; L _pp - full range of rudders, m; L _RKR - full wingspan, m;

- the relative distance between the axis of rotation of the steering wheel and the tip of the side chord of the wing; L _cr - the distance from the nose of the rocket to the nose of the side chord of the wing, m; L _ovr - the distance from the tip of the rocket to the axis of rotation of the steering wheel, m; L _corp - rocket body length, m 5. The rocket according to claim 1, containing a propulsion system with a diameter equal to 1.1 ... 1.3 of the diameter of the hull, which has the following size ratios:

Where

- the ratio of the full span of the rudders and wings; L _pp - full range of rudders, m; L _RKR - full wingspan, m;

- the relative distance between the axis of rotation of the steering wheel and the tip of the side chord of the wing; L _cr - the distance from the nose of the rocket to the nose of the side chord of the wing, m; L _ovr - the distance from the tip of the rocket to the axis of rotation of the steering wheel, m; L _corp - rocket body length, m 6. The rocket according to claim 1, in which the steering gears are made hydraulic with power from a pump-storage system.

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