RU2280836C1 - Method for protection of flight vehicles against guided missiles and system for its realization - Google Patents

Abstract

FIELD: armament and military equipment, in particular, protection of aircraft against attacking guided missiles, for example, with the aid of machine-gun (gun) mountings.

SUBSTANCE: in the known method for protection of flight vehicles against guided missiles including a search, detection and tracking of the guided missile, determination of angular corrections of the means of destruction of the guided missile for determination of its spatial attitude, the destructive action on the guided missile with regard to the determined corrections, according to the invention before the beginning of the destructive action of the means of destruction the most attack-dangerous guided missile is selected out of the attacking ones and the required miss of the separated guided missile, range to the initiation of the flight vehicle maneuver (Dinm) and the range of the destructive action are determined, the destructive action is performed at the range of the destructive action, after that at the range of the beginning of the destructive action determined from a mathematical expression the maneuver of the flight vehicle is performed with an allowable g-load up in the vertical plane up to the fly-by of the guided missile. The raised task is solved by the fact that in the known system of fire protection against a guided missile containing the series-connected scanning-sighting system, on-board computer, power drives of the installation, destruction means, as well as the navigation, destruction means as well as the navigation system, the outputs of the navigation system are connected to the computer inputs, according to the invention additionally used are a device for selection of the maneuver and firing ranges, a comparison unit, a unit for formation of the maneuver and firing ranges, as well as a unit for formation of the flight time. The first and the second inputs of the unit for formation of the line range are connected respectively to the second and the third outputs of the scanning-sighting system, the third input of the unit for formation of the line range is connected to the first output of the navigation system, its fourth input is connected to the output of the unit for formation of the flight time, and the fifth input of the unit for formation of the line range - to the first output of the comparison unit, whose first input is connected to the first output of the scanning - sighting system, its second and the third inputs receive signals from the selectors of the required miss value and allowable g-load of the flight vehicle. The fourth input of the comparison unit is connected to the output of the unit for formation of the flight time, the first and the second inputs of the unit for formation of the flight time are connected to the second and the third outputs of the scanning-sighting system respectively, its third input is connected to the first output of the comparison unit, the fourth and the fifth inputs of the unit for formation of the flight time are connected respectively to the first and the second outputs of the navigation system, its sixth and seventh inputs receive signals from the selectors of the values of the ballistic coefficient and the missile initial speed respectively. The first input of the unit for formation of the maneuver and firing ranges is connected to the first output of the navigation system, its second, third and fourth inputs are connected respectively to the second, third and first outputs of the scanning-sighting system, the fifth, sixth and seventh inputs of the unit for formation of the maneuver and firing ranges receive signals from the selectors of fire rate N, burst length and missile speed respectively, its ninth input is connected to the output of the unit for formation of the flight time, and the tenth input - to the sixth output of the navigation system, the first output of the unit for formation of the maneuver and firing ranges is connected to the input of the flight vehicle control system, and its second output - to the input of the destruction means.

EFFECT: enhanced survival rate of the flight vehicle due to maximum reduction of the firing range by the fire protection system and thus provision of the required systematic miss of the destructed missile due to maneuver of the flight vehicle.

10 cl, 8 dwg, 1 tbl

Description

The invention relates to the field of weapons and military equipment, in particular, to the protection of an aircraft from guided missiles (UR) attacking it, for example, using machine-gun (cannon) defensive installations.

An analysis of the literature shows that there is a way to protect a defended aircraft (OS), which consists in obtaining information about attacking targets with the help of warning equipment, fixing the launch moment of the missile defense and anti-ballistic maneuver [1].

To implement this method on modern airplanes, in particular front-line fighters, there is a subsystem for threat detection and countermeasures, including warning equipment for radiation and direction finding of enemy ground and airborne stations, heat direction finders, the task of which is to fix the flare of the UR launch engine, an information processing system computer and management [2].

The disadvantages of the above method and its implementing system are as follows. First, to obtain misses of several tens of meters required for OS safety, it is necessary to maneuver with overloads of the order of _nos = 8-10 units, which is available only for highly maneuverable "light" aircraft.

Secondly, for missiles of maneuverable air combat, the main task of which is to defeat an intensely maneuvering target, a dynamic miss even with n _oc = 8-10 units. is close to 0 and reaches a conditional maximum at τ≤1 s (where τ is the time before the UR meets the OS) due to the high available overload and the broadband circuit.

In other words, the applied method is ineffective in repelling the attack of highly maneuverable SDs, since the required amount of systematic miss is not provided.

There is also a way to increase OS survival, which consists in obtaining information about attacking targets using warning equipment, fixing the moment of launching SDs, launching false targets (for example, firing cartridges with dipole reflectors and IR tracers) and (or) setting up active interference by electronic warfare [3, 4].

To implement this method on almost all modern domestic and foreign aircraft, an automated system for counteracting and creating interference is organized, which includes equipment for detecting working radars, equipment for recording the moment of launching enemy missiles (direction finders), active jamming stations, IR jammers, ejection machine dipole reflectors [2].

The disadvantages of this method and its implementing system are as follows. First, at the modern level of technology for creating interference and noise immunity of homing heads (GOS), the probability of failure to track the target of a modern noise-protected GOS is negligible, and the effectiveness of the interference is determined only by the degree of impact on the SD control system and the accuracy of its homing. Secondly, the use of false targets, such as firing cartridges with dipole reflectors and IR tracers, firing forward or towing false targets, requires significant weights and aircraft to be allocated to the OS, which leads to a decrease in the flight qualities of the carrier.

The closest technical solution, selected as a prototype, is a way to protect the OS from attacking targets, which consists in searching, detecting and tracking the target with an aiming and navigation system with the necessary parameters being output to the on-board computer, determining angular corrections with working out the power means of the destruction and their impact on the target means of destruction [5].

The known fire protection system (POPs) of an aircraft, selected as a prototype of the claimed system, contains a series-connected survey and aiming system, an on-board counting and resolving device, power drives of a weapon, a weapon, and a navigation system, the outputs of the navigation system being connected to the inputs computing device [5].

The disadvantage of this method and the system that implements it is that it does not provide acceptable OS survival due to the long firing ranges necessary to form the required, based on OS security, the systematic miss of the affected UR.

The objective of the proposed method and the system that implements it is to increase the survival of the aircraft by limiting the range of POPs to a maximum and thereby ensure the necessary systematic miss of the affected urine due to the maneuver of the aircraft.

This object is achieved by the fact that in the known method of protecting aircraft (LA) from guided missiles (SD), which includes searching, detecting and tracking SD, determining angular corrections of the weapon of destruction of the SD to determine its spatial position, the damaging effect of the SD, taking into account certain amendments , according to the invention, in addition to the start of the damaging effect, the means of destruction emit the most hazardous of the attacking SDs and determine the required miss h ^{loss of the} allocated SDs, LA neuron D _nm and the damaging effect D _n , while the damaging effect is produced at a range of D _n , after which at a range of D _nm maneuver of the aircraft is carried out with overload n _os up in the vertical plane before the span of the SD.

The task is also achieved by the fact that h ^loss , D _nm and D _{n are} determined from the ratios:

where D _y , D _p - respectively, the anticipated range of the last shot and the range of the line, m,

t _y - flight time of the projectile, s,

n _OS - permissible aircraft overload, units,

v _OS , v _p - speed, respectively, aircraft and SD, m / s,

β, ε - target viewing angles in the coordinate system associated with the carrier, rad,

- скорость сближения УР и ЛА, м/с,

- approach speed of UR and LA, m / s,

g is the acceleration of gravity, m / s ² ,

K ₁ (K ₂ ) - approximation coefficients t _y (D _y ), m / s (s / m ² ),

v ₀₁ , c _H - respectively, the absolute velocity and reduced ballistic coefficient of the projectile, m / s, m ² / kgf,

n _Pts - the length of the queue, rds.,

N - rate of fire, rds / min,

h ^rub - the required miss of the most hazardous identified SD.

The task is achieved by the fact that in the known system of fire protection of aircraft from UR, containing sequentially connected sighting and sighting system, onboard counting and resolving device, power drives of the installation, means of destruction (SP), as well as a navigation system, and the outputs of the navigation system are connected to the inputs of the computing device according to the invention additionally introduced a device for selecting ranges of maneuver and firing, containing a series-connected unit for forming the range of the line, a comparison unit, bl to the formation of maneuver and firing ranges, as well as the flight formation formation unit, the first and second inputs of the range formation unit are connected respectively to the second and third outputs of the sighting system, the third input of the formation range formation line is connected to the first output of the navigation system, its fourth the input is connected to the output of the flight time formation unit, and the fifth input of the boundary range formation unit is connected to the first output of the comparison unit; the first input of which is connected to the first output of the sighting system, its signals are supplied to the second and third inputs according to the required value of miss h ^sp and allowable overload of the aircraft n _os , the fourth input of the comparison unit is connected to the output of the flight time formation unit, the first and second the inputs of the flight time formation unit are connected respectively to the second and third outputs of the sighting system, its third input is connected to the first output of the comparison unit, the fourth and fifth inputs of the formation unit Hovhan flight time are respectively connected to first and second outputs of the navigation system, the sixth and seventh its inputs receives signals with setpoint values, respectively, the ballistic coefficient and muzzle velocity v _0, the first input unit forming distances maneuver and firing is coupled to the first output of the navigation system, its second, third and fourth inputs are connected respectively to the second, third and first outputs of the sighting system, to the fifth, sixth and seventh inputs of the forming unit alnostey maneuver and firing receives signals from setting devices respectively rate of fire N, queue length n _och and missile speed v _p, the ninth its input connected to the output of the forming flight time, and the tenth - a sixth output of the navigation system, a first output forming unit ranges maneuver and firing is connected to the input of the aircraft control system, and its second exit is to the input of the joint venture.

The task is also achieved by the fact that the block forming the range of the boundary is made in the form of series-connected first multiplying devices, a block for converting the cosine of an angle to sine, a second multiplier device, a block for converting the sine of an angle into cosine, an adder and a third multiplying device, as well as a series-connected fourth the fifth and sixth multiplier devices, and the first and second inputs of the first multiplier device are connected respectively to the outputs of the first and second shackles determining the cosine of the angle (cosine transformers) and its output - to the second input of the sixth multiplier device, the output of the fifth multiplier device connected to the second input of the second multiplier unit, the output of the sixth multiplier device connected to the inverse second input of the adder; the inputs of the first and second cosine converters are connected respectively to the second and third outputs of the sighting system, the first and second inputs of the fourth multiplier device are connected respectively to the output of the flight time generation unit and the first output of the comparison unit, the first output of the comparison unit is also connected to the second input of the third multiplier device, the second input of the fifth multiplying device is connected to the first output of the navigation system.

и с задатчиком требуемого промаха h^потр.The task is also achieved by the fact that the comparison unit is made in the form of series-connected first divider, first quadrator, first adder, first multiplier device and extremum search unit, as well as series-connected second adder, second quadrator and second multiplier, the first and second the inputs of the second adder are connected respectively to the output of the first divider and to the output of the flight time generation unit, and the output of the second multiplying device nen with the second input of the first adder, the first and second inputs of the first divider are connected respectively to the output of the block forming the range and the first output of the sighting system, the second input of the second multiplying device receives a signal from the master of the permissible overload of the aircraft _nos , second and inverse third the inputs of the search block of the extremum of the function are connected respectively with the setter of the initial value of the anticipated range

and with the master of the required miss h ^rub .

The task is also achieved by the fact that the flight time formation unit is made in the form of series-connected relative air density formation unit, a first multiplier device, a first approximation coefficient formation unit, a divider, and second, third and fourth multiplier devices, a first adder, and a series-connected unit extraction of the square root and the second block of the formation of the approximation coefficient, as well as sequentially connected to the first square a fifth multiplier device of the second adder, the second input of the first approximation coefficients forming unit connected to the output of the square root extraction unit, and the first input of the second approximation coefficient forming unit - with output of the first multiplier device divider output coupled to an input of the second adder; the second input of the fifth multiplying device is connected to the output of the second approximation coefficient generating unit; the first and second inputs of the first adder are connected to the outputs of the second and third quadrators, respectively; a signal from the first output of the navigation system is supplied to the input of the second quadrator and the second input of the second multiplier device, a signal from the initial speed adjuster v ₀ is supplied to the input of the third quadrator and to the first input of the second multiplier device; the first input of the fourth multiplying device is connected to the output of the sixth multiplying device, the inputs of which are connected to the first and second cosine converters, the inputs of which are connected respectively to the second and third outputs of the sighting system; the input of the unit for forming the relative density of air is connected to the second output of the navigation system; the second input of the first multiplying device is connected to a ballistic coefficient setter c; the first input of the divider and the input of the first quadrator are connected to the first output of the comparison unit.

The stated task is also achieved by the fact that the maneuvering and firing range formation unit is made in the form of a first multiplier device, an angle to sine cosine conversion unit, a second multiplier device, a first quadrator, a first adder with an inverse input, a first square root extraction unit, and a second adder , a third multiplier, a third adder, a range comparison element, and a fourth multiplier, connected in series, second the fourth quadrator, the fourth adder with the inverse first input, the second square root extracting unit, the fifth multiplier device, as well as the firing rate setter N, the first divider and the sixth multiplier device, the first input of the fourth multiplier device being connected to the output of the cosine angle to sine, the second input of the second adder is connected to the output of the fifth multiplier, the second input of the third adder is connected to the output of the sixth multiplier Islands; the second input of the second multiplier device is connected to the output of the seventh multiplier device, the first input of which is connected to the output of the second divider, the first input of which is connected to the second output of the comparison unit, and the second input to the output of the flight time generation unit, the second input of the fifth multiplier is connected to the output the second divider, the second inputs of the fourth and seventh multiplying devices are connected to the first output of the navigation system, the first and second inputs of the first multiplying device are connected s, respectively, the first and second cosine converters whose inputs are connected respectively to the third and second outputs of surveillance-aiming system, the second fourth adder input connected to the output of the third squaring, to the input of which is fed a signal from setpoint v _p missile velocity, the second input of the third multiplier device connected to the second output of the comparator, the second input of the first divider is connected with setpoint _och queue length n, a second input of the sixth multiplier device connected to the first output Panoramic -pritselnoy system, and the second input range comparison element - a sixth output of the navigation system.

The stated task is also achieved by the fact that the maneuvering and firing range formation unit is made in the form of a first quad, a first multiplier, a first adder, a square root extraction unit, a second multiplier, a second adder, a third multiplier, a third adder, and a range comparison element , as well as sequentially connected firing rate setter N, the first divider, the fourth multiplying device, the output of which is connected to a third by an adder, wherein the inverse second input of the first multiplier is connected to the output of the second quadrator, the input of which is connected to the first output of the navigation system, the second input of the first adder is connected by the output of the third quadrator, the input of which is connected to the rocket speed adjuster v _p , the second input of the second multiplier is connected with the output of the second divider, the first input of which is connected to the second output of the comparison unit, and the second input of the second divider is connected to the output of the flight time formation unit , the input of the first quadrator is connected to the output of the block transforming the cosine of the angle into sine, which, in turn, is included in the block forming the range of the line, and the second input of the second adder is connected to the output of the block transforming the sine of the angle into cosine, which, in turn, is also in the block formation of the range of the line; the second input of the third multiplier device is connected to the second output of the comparison unit, the second input of the first divider is connected to the setter of the queue length n _och , the second input of the fourth multiplier device is connected to the first output of the sighting system, and the second input of the range comparison element is connected to the sixth output of the navigation system .

In a particular case, the means of destruction is a machine gun (cannon) installation.

In a particular case, the means of destruction is a combat laser installation.

Namely, the values of the ranges D _nm and D _n determined with the help of an additional block and realized during reflection of an attack by SD ensure according to the method the aircraft's survival and thereby achieve the goal of the inventions. This allows us to conclude that the claimed invention is interconnected by a single inventive concept.

A comparative analysis of the claimed solutions with the prototypes shows that the claimed method differs from the known one in that prior to the shooting, identifying and identifying the most attacking target, the required miss of the affected SD (SD with a damaged control system (SU)) is determined relative to the protected aircraft, for example, OS , from the condition of ensuring the probability of an aircraft damage from detonation of a non-contact fuse of a missile defense with damaged AS during an aircraft flight close to 0 (see Fig. 1)

where R _then - the probability of damage to the LA of the UR with damaged SU,

- функция Бесселя первого рода нулевого порядка,Where

- Bessel function of the first kind of zero order,

h is the systematic component of the miss,

σ = σ ^UR - standard deviation of random miss UR,

d _f - reduced diameter of the aircraft (for example, the fuselage of the OS).

в круг радиуса

.As follows from the above dependence for the calculation, the problem of determining R _then in this case is reduced to finding the probability of hit by SD, the dispersion of which in the picture plane is subject to the Rice law

in a circle of radius

.

To identify the characteristics of: the damaging effect of SD _UR (R _UR = min (R _warhead , R _blast ), where R _warhead and R _blast are the radius of action of the warhead and fuse of the SD, respectively) and dispersion σ _UR - first it is necessary to isolate the most hazardous of attackers and identification of SD, for example, by the size of the effective scattering area, the degree of aerodynamic heating, the approach speed, size, launch range, etc. [6].

Entering into the on-board computer system (VVS) using the on-board sensors of the aiming and navigation system, the required information about the parameters of the target and carrier movement, external conditions (1, 2), as well as data about the weapon (3) (for example, the cannon mount) scheme:

- соответственно дальность, м, и скорость сближения ЛА и УР, м/с,where D

- respectively, the range, m, and the approach speed of the aircraft and SD, m / s,

β, ε are the angular coordinates of the target in the coordinate system associated with the carrier (see figure 2),

ω _YD , ω _ZD are the angular velocities of the line of sight relative to the axes of the sighting coordinate system OY _D and OZ _D , rad / s (see figure 2),

v _OC - carrier speed, m / s,

N (N) is the relative density of air,

s, v ₀ - respectively, the ballistic coefficient, m ² / kgf, and the initial velocity of the projectile, m / s,

N - rate of fire, rds / min,

preliminarily calculate the velocity of the SD v _p , m / s, depending

then using the proposed additional device for selecting the ranges of the beginning of maneuver and firing (see Figs. 3-4), we determine the rational ranges of the beginning of the maneuver D _nm and the beginning of firing D _n from the relations:

where D, D _y , D _p - respectively, the range of sight of the target, the anticipated range of the last shot and the range of the line, m,

t _y - flight time of the projectile, s,

n _OS - permissible aircraft overload, units,

v _oc , v _p - speeds, respectively, of the aircraft and SD, m / s,

β, ε - target viewing angles in the coordinate system associated with the carrier, rad,

- скорость сближения УР и ЛА, м/с,

- approach speed of UR and LA, m / s,

g is the acceleration of gravity, m / s ² ,

K ₁ (K ₂ ) - approximation coefficients t _y (D _y ), m / s (s / m ² ),

v ₀₁ , c _H - respectively, the absolute velocity and reduced ballistic coefficient of the projectile, m / s, m ² / kgf,

n _Pts - the length of the queue, rds.,

N - rate of fire, rds / min,

h ^rub - required miss of the most dangerous identified SD.

Shooting is carried out at a pre-calculated (see above) rational range (D _n ), which depends on the parameters of the target and carrier movement, the external environment, the characteristics of the weapon, the type of attacking SD, the parameters of its striking effect and accuracy.

.At the end of firing at a pre-calculated range of D _nm , the OS maneuvers with permissible overload

.

Comparison of the claimed technical solutions with prototypes allows us to establish compliance with the criterion of "novelty."

Analysis of the known methods of aircraft protection in this and related fields of technology does not allow us to identify in them a combination of features that distinguish the claimed solution from the prototype.

Target identification operations, target striking effects by firing PU [5] or laser radiation [9, 10], aircraft maneuvers are widely known. However, when they are introduced into the method in the indicated sequence (connection) at pre-calculated rational ranges (or strictly at certain points in time), the desired effect is achieved - increased survival of the aircraft.

In the study of other well-known technical solutions in this technical field, the signs that distinguish the claimed invention is the fire protection system of the aircraft from the prototype, were also not identified.

This allows us to conclude that the proposed solutions meet the criterion of "significant differences".

The positive effect is achieved due to the optimal combination of firing defensive launchers (the damaging effects of the laser system) and the OS maneuver. In order not to increase shooting errors, it is advisable to start the maneuver immediately after the shooting.

. Во-вторых, и это основная цель маневра, обеспечивается дополнительный вклад в систематическую составляющую промаха.At the same time, they achieve a double effect. Firstly, the conditions for guidance of the SD are deteriorating due to the emergence of unsteady guidance modes of SD in the final section, with any guidance methods

. Secondly, and this is the main goal of the maneuver, an additional contribution to the systematic component of the miss is provided.

Figure 5 is a diagram illustrating the process of forming a missed SD with damaged SU relative to an aircraft, for example, an operating system.

The systematic component of the miss is ensured by two components: “sagging” of the damaged SD (h ₁ ) and due to the OS maneuver at the end of the shooting (h ₂ )

where D _p is the range of the line (between the point of destruction of the SD and the plane at the time of the defeat of the SD), m,

- скорость сближения УР и ОС, м/с,

- the convergence rate of UR and OS, m / s,

t _y - flight time of the projectile at a range of D _y , s,

where D _y - anticipated (flight range of the last shot),

β, ε are the viewing angles of the target in the coordinate system associated with the carrier (LA),

Δβ, Δε - angular corrections of firing.

An example of the calculated dependences Δβ and Δε and their implementation are given, in particular, in [5].

It should be noted that the above equations are related, because t _y = t _y (c _H D _y , v ₀₁ ), v ₀₁ = v ₀₁ (v _OS , v ₀ , β ', ε'), β '= β + Δβ, ε' = ε + Δε, Δβ = Δβ (D), Δε = Δε (D), therefore, these equations must be solved together. However, taking into account that the values of Δβ and Δε are small at the ranges studied by us (D _nm ≅ 100-400 m) in comparison with the values of β and ε, cosβ'≅cosβ, cosε'≅cosε can be set with sufficient accuracy for calculations.

This allows us to simplify the search process for D _nm and, as will be shown below, it becomes possible to reduce it to a sequential solution to the solution of nonlinear algebraic equations.

From the ABC preemptive triangle, by the sine theorem, we can write:

where ψ _p , ψ _sn - lead angles respectively UR and projectile.

,

, где q - курсовой угол (угол между скоростью ОС и линией визирования D, см. фиг.5), можно записать:After intermediate calculations using trigonometric transformations and taking into account the dependencies

,

, where q is the heading angle (the angle between the speed of the OS and the line of sight D, see figure 5), you can write:

From the preemptive triangle BCD, by the sine theorem, we can write:

By analogy with the above reasoning, we obtain:

, с помощью которой устанавливается взаимосвязь между потребной перегрузкой ОС n_ос при маневре, упрежденной дальностью окончания стрельбы Dy (упрежденная дальность последнего выстрела) и вероятностью выживания ОС при отражении атаки УР

.According to the algorithm obtained in this way, taking into account the miss miss h ^loss required for each SD target, lines of equal misses are constructed. In Fig.6 as an example, the nomogram

, with the help of which a relationship is established between the required OS overload n _os during maneuver, the anticipated firing range Dy (the anticipated range of the last shot) and the probability of the OS surviving when repulsing an SD attack

.

, для D_у=180 м находим обеспечиваемое при этом значение

при σ_т.р.=3 мрад. Время маневра при этом составляет t_м=0.7 с. Для сравнения при n_ос=0

.Entering the schedule _nos -D _y with the value of the permissible overload set for the given OS, for example, _nos = 6 units, we find the range of the start of the maneuver corresponding to the anticipated range of the last shot of the defensive launcher. For the UR “AMRAAM” (h ^spr = 18 m) this value is D _nm = D _y = 180 m. Next, going to the graph

, for D _у = 180 m, we find the value provided

at σ _tr = 3 mrad. The maneuver time is t _m = 0.7 s. For comparison, when n _OS = 0

.

The maneuver and firing ranges selected using the proposed ratios are rational, since reducing them will lead to a sharp increase in OS safety due to the detonation of a non-contact fuse with a damaged control system during flight. On the other hand, an increase in these ranges will reduce the likelihood of shells entering the SD (in the case of launchers). An increase in the range at which the target of the combat laser system is targeted leads to an increase in the required laser power, and consequently, its mass, dimensions and cost.

от дальности D_у для СОЗ на базе двух 6-мм пулеметов ТКБ-764 (N_∑=2×10000 выстр./мин, v₀=1050 м/с, σ_т..р=3 т.д.) при отражении так УР типа «Феникс», «AMRAAM» и «Сайдвидер», на рис.7б -

для СОЗ на базе 57 мм пушки ТКБ-776 (N=900 выстр./мин, v₀=500 м/с, σ_т.р.=4 мрад).On figa as an illustration built the dependence of the probability of survival of the OS

from the range D _y for POPs based on two 6-mm machine guns TKB-764 (N _∑ = 2 × 10,000 rds / min, v ₀ = 1050 m / s, σ _{tp p} = 3 etc.) when reflected So URs like “Phoenix”, “AMRAAM” and “Sidevider”, on fig.7b -

for POPs based on a 57 mm TKB-776 gun (N = 900 rds / min, v ₀ = 500 m / s, σ _tr = 4 mrad).

(против

при n_ос=0), УР «AMRAAM» 0.7 (против

при n_ос=0) и УР «Феникс» 0.83 (против

при n_ос=0).As seen from the graphs, when short maneuvering OS (Δt = 0.7-1.2 c) with an overload n _oc = 6 units. POPs on the basis of two coaxial machine guns TKB-764 provides the probability of OS survival when reflecting UR “Sidewinder”

(against

with n _os = 0), UR "AMRAAM" 0.7 (against

with n _os = 0) and UR "Phoenix" 0.83 (against

with n _os = 0).

, УР «AMRAAM»

и УР «Феникс»

.An increase in the permissible overload OS to n _oc = 8 units. increases OS survival to the following levels: when reflecting UR “Sidewinder”

, UR "AMRAAM"

and UR "Phoenix"

.

(УР «AMRAAM») можно увеличить с

(

при n_ос=0) до

(

при n_ос=2 ед.). Время маневра t_м≅1.2 c.From ris.7b that even using maneuver overload n _a = 2 pcs., Are achievable for "heavy aircraft", equipped with POPs based on a 57-mm gun TKB-776 missiles with non-contact action, the probability of survival of the OS

(UR "AMRAAM") can be increased from

(

when n _OS = 0) to

(

when n _OS = 2 units). Maneuver time t _m ≅1.2 s.

Thus, the proposed method and device for its implementation have a positive effect - increased OS survival and can be used in a wide class of carriers (LA) and their fire protection systems.

Figure 1 shows the dependences of the probability of damage to the OS during the passage of a missile defense with a damaged SU R _then the miss h for a missile defense of the type “Sidewinder”, “AMRAAM” and “Phoenix” according to the dependence (*) (see the description of page 11) and the initial data given in the table (column 1, 2).

Table Type of UR Sidewinder AMRAAM "Phoenix" R _then M 5 9 fifteen σ _UR , M 3 four 7 H ^rub , m 12 eighteen thirty

систем координат (с.к.) относительно связанной (с носителем) с.к. X_нY_нZ_н.Figure 2 shows the orientation of the target X _D Y _D Z _D and associated with a movable artillery installation

coordinate systems (c.c.) relative to associated (with carrier) s.c. X _n Y _n Z _n

S.K. X _n Y _n Z _{n is} rigidly connected to the center of mass of the carrier aircraft. The axis OX _{n is} directed along the longitudinal axis of the aircraft in the direction of flight, the axis OY _n is in the plane of symmetry of the OS upward perpendicular to the plane X _n OZ _n , and for the positive direction of the axis we take the direction to the right.

S.K. X _D Y _D Z _D is connected to the target tracking system (sighting device). The axis OX _{D is} directed along the axis of the range. S.K. X _D Y _D Z _{D is} formed from s.k. X _n Y _n Z _{n in} two rotations: a) around the axis OY _n by an angle β in the plane of the wings of an airplane; and b) around the axis OZ _D in a plane perpendicular to the plane of the wings by an angle ε.

связана с подвижной ПУ. Ось

направлена по оси ствола пушки по вектору v₀. С.к.

образуется из с.к. Х_нY_нZ_н двумя поворотами: а) вокруг оси вращения, параллельной оси OY_н самолета на угол β', б) вокруг оси

на угол ε'.S.K.

connected with mobile PU. Axis

directed along the axis of the gun barrel along the vector v ₀ . S.K.

formed from s.k. X _n Y _n Z _{n in} two rotations: a) around the axis of rotation parallel to the axis OY _{n of the} aircraft at an angle β ', b) around the axis

angle ε '.

Figure 3 presents the proposed functional diagram of the POPs of the aircraft:

1 - survey and sighting system; 2 - radar survey and sighting station; 3 - optical sighting station; 4 - navigation system; 5 - calculating and solving device; 6 - a device for selecting ranges of maneuver and firing; 7 - block forming the range of the border D _p ; 8 - block comparison; 9 - block forming flight time t _y ; 10 - block forming the ranges of the beginning of the maneuver and the start of firing; 11 - power drive installation; 12 - aircraft control system; 13 - aircraft; 14 - cannon (machine-gun) installation (or combat laser installation).

Figure 4 gives a detailed structural diagram of the blocks of the device 6, built on analog elements.

The signals D _nm and D _n at the output of the device 6 are formed as follows.

Block forming the range of the border D _p 7.

The angular coordinates β and ε are received at the inputs of the first and second cosine converters from the sighting station 1. At its output, signals cosβ and cosε are formed, respectively, which, in turn, are fed to the input of the first multiplying device (MU) MU1, where they multiply. The product cosβ · cosβε = cosq obtained at the MU1 output is fed to the input of the cosine-sine converter, where the sinq signal is generated.

поступает на вход пятого МУ МУ 5, на второй вход которого с навигационной системы 4 подается значение v_oc. После перемножения этих сигналов в блоке МУ5 образуется сигнал

, который подается на второй вход второго МУ-МУ2, где происходит перемножение его на sinq, поступающий с выхода косинусно-синусного преобразователя. Полученный на выходе МУ2 сигнал cosψ_сн поступает на вход синусно-косинусного преобразователя, на выходе которого формируется сигнал, который суммируется в сумматоре (СУМ) с предварительно инвертированным сигналом

. Полученная на выходе СУМ разность

поступает на вход третьего МУ-МУ3, где перемножается с сигналом D_у, поступающим с выхода блока сравнения 8, в результате на выходе МУ3 формируется выходной сигнал блока формирования дальности рубежа 7

.At the same time, an electric signal corresponding to D _{y is} received from the comparator 8 at the input of the fourth MU-MU4, and a signal t _{y is} received from the output of the flight time generating unit 9, where division occurs. Signal

arrives at the input of the fifth MU MU 5, the second input of which from the navigation system 4 is supplied with the value v _oc . After multiplying these signals in the block MU5, a signal is generated

, which is fed to the second input of the second MU-MU2, where it is multiplied by sinq, coming from the output of the cosine-sine converter. The signal cosψ _sn received at the output of MU2 is fed to the input of the sine-cosine converter, the output of which generates a signal that is summed in the adder (SUM) with a previously inverted signal

. The difference obtained at the output of the SUM

arrives at the input of the third MU-MU3, where it is multiplied with the signal D _y coming from the output of the comparison unit 8, as a result, the output signal of the unit for forming the range of the boundary of 7 is formed at the output of the MU3

.

Comparison Block 8.

. После деления в Д1 D_p на

сигнал

поступает вход первого квадратора К1, где образуется сигнал

, и на вход второго СУМ СУМ2, на второй вход которого поступает сигнал t_y с выхода блока формирования полетного времени 9. На выходе СУМ2 формируется сумма

, которая далее поступает на вход второго квадратора К2, на выходе которого формируется сигнал

. Этот сигнал поступает на первый вход второго МУ - МУ2, на второй вход которого летчиком задается допустимое значение перегрузки ЛА n_ос. В результате перемножения на выходе МУ2 формируется сигнал

который поступает на второй вход первого сумматора СУM1, на выходе которого формируется сумма (с одновременным перемножением на коэффициент

)

Этот сигнал вычитается из задаваемого на вход блока поиска экстремума (extr) сигнал h^потр.The signal D _p generated at the output of the unit for forming the range of the boundary of D _p 7 is fed to the first input of the first divider D1, a signal is received at its second input from sighting station 1

. After dividing in D1, D _p by

signal

the input of the first quadrator K1 is received, where a signal is formed

, and to the input of the second SUM SUM2, the second input of which receives a signal t _y from the output of the flight time generation unit 9. At the output of SUM2, the sum

, which then goes to the input of the second quadrator K2, at the output of which a signal is formed

. This signal is fed to the first input of the second MU - MU2, the second input of which the pilot sets the permissible value of the aircraft overload n _OS . As a result of multiplication at the output of MU2, a signal is formed

which goes to the second input of the first adder СУМ1, at the output of which a sum is formed (with simultaneous multiplication by a coefficient

)

This signal is subtracted from the input of the extremum search block (extr) signal h ^rub .

в блоке поиска экстремума сравнивается с заданной точностью ε^зад. При выполнении условия ε≤ε^зад полученное значение D_у является выходным и передается по выходу 2 в блок формирования дальностей начала маневра и начала стрельбы 10.Difference obtained

in the extremum search block is compared with the given accuracy ε ^ass . When the condition ε≤ε is fulfilled, the ^{ass of the} obtained value of D _y is the output and is transmitted to the output unit 2 in the unit for forming the ranges of the beginning of the maneuver and the beginning of firing 10.

и передается по выходу 1 на новую итерацию в блок формирования полетного времени, цикл повторяется [8].In the case of the condition ε> new value generated e ^ass

and is transmitted at exit 1 to a new iteration in the flight time generation unit, the cycle repeats [8].

Block formation flight time t _at 9.

At the input of the unit for forming the relative density of air N (N) from the navigation system 4, the value of the flight altitude OS N is received, where the value of the relative density of air N (N) is selected, it is fed to the input of the first multiplier device MU1, the second input of which is started with the PSA ballistic coefficient c. After multiplication in MU1, the value c _Н = с × Н (Н) is obtained, which is supplied to the first inputs of the approximation coefficient formation blocks K ₁ (c _н , v ₀₁ ) and К ₂ (с _н , v ₀₁ ), to the second inputs of which the value of the absolute initial velocity v ₀₁ , which is formed as follows. The input velocity of the carrier v _{oc is} received from the navigation system at the input of the second quadrator K2 and the second input of the second multiplier device MU2, and the value of the initial velocity of the projectile v ₀ is fed to the input of the third quadrator and the first input MU2, the output of which is the product v ₀ · v _oc , which, doubling in the third MU-MU3, enters the second input of MU4. The first input of MU4 receives the product cosβ · cosε = cosq from the output of MU6, formed using two cosine converters from the signals β and ε supplied to their inputs from the sighting system 1-3.

и

соответственно с К2 и К3. На выходе СУM1 образуется сумма

, которая поступает на вход блока извлечения корня √, на выходе которого формируется сигнал

, который поступает на вторые входы первого и второго блоков формирования коэффициентов аппроксимации, где формируются сигналы соответственно K₁=К₁(c_H,v₀₁) и К₂=К₂(с_Н,v₀₁), поступающие далее на вторые входы соответственно делителя Д и МУ5.After multiplying in MU4 the two signals received at its input, a signal 2 · v _oc · v ₀ · cosβ · cosε is formed at its output, which is fed to the third input of СUM1, the first and second inputs of which receive signals, respectively

and

respectively with K2 and K3. At the output of СУМ1, the sum

, which is input to the root extraction unit √, at the output of which a signal is generated

, which goes to the second inputs of the first and second blocks of the formation of approximation coefficients, where signals are formed, respectively, K ₁ = K ₁ (c _H , v ₀₁ ) and K ₂ = K ₂ (with _H , v ₀₁ ), which then go to the second inputs, respectively divider D and MU5.

и

. Сформированное в СУМ2 значение

является выходным сигналом блока формирования полетного времени 9.The first and second inputs of SUM2 receive signals from the outputs, respectively, D and MU5

and

. Formed in SUM2 value

is the output signal of the unit forming the flight time 9.

The unit for forming the ranges of the beginning of the maneuver and the beginning of firing 10.

поступает на первый вход седьмого МУ (МУ7) и на второй вход МУ5. В МУ7 происходит перемножение

на величину v_oc, поступающую на второй его вход. Образующийся на выходе блока МУ7 сигнал

поступает на второй вход МУ2.At the first input of the divider 2 D2 from the first output of the comparison unit 8, the value D _{y is} received, and at its second input from the output of the unit for the formation of flight time t _y 9, the value t _y . The signal generated at the output of D2

arrives at the first input of the seventh MU (MU7) and at the second input of MU5. In MU7, multiplication occurs

by the value of v _oc entering its second input. The signal generated at the output of the MU7 unit

arrives at the second input of MU2.

. В СУМ 4 происходит суммирование его с сигналом

, получаемым с третьего квадратора К3, на вход которого подается с СРП 5 значение v_p.Simultaneously with the output of the aiming system 1-3, the values of β and ε are received at the inputs of the cosine converters. The resulting values of cosβ and cosε are fed to the input of MU1, where they are multiplied, the signal cosβ × cosε = cosq is fed to the input of the cosine-sine converter, from the output of which the signal sinq is fed to the first inputs of MU2 and MU4. After multiplying sinq by the value of v _oc coming to the second input of MU4, squaring the received signal into a square in the second quadrator K2 and inverting, we send the signal to the first input of SUM4 -

. In SUM 4, it is summed with a signal

obtained from the third quadrator K3, the input of which is supplied with PSA 5 value v _p .

поступает на вход второго блока извлечения корня √₂, где происходит извлечение корня. Сформированный таким образом сигнал перемножается в МУ5 с сигналом

- и поступает на вход СУМ2.The signal received at the output of SUM4

arrives at the input of the second root extraction unit √ ₂ , where the root is extracted. The signal thus formed is multiplied in MU5 with the signal

- and enters the SUM2 input.

с выхода МУ7. Полученный на выходе МУ2 сигнал, проходя через первый квадратор K1 (sin²ψ_сн) в СУМ1 вычитается из единицы (1-sinψ_сн) и поступает на вход первого блока извлечения корня √₁, на выходе которого образуется сигнал

, который поступает на вход СУМ2.In MU2 there is a multiplication of those entering the first input sinq and the second input

from the exit of MU7. The signal received at the output of MU2, passing through the first quadrator K1 (sin ² ψ _sn ) in SUM1 is subtracted from unity (1-sinψ _{сн sn} ) and fed to the input of the first root extraction unit √ ₁ , at the output of which a signal is generated

, which goes to the input of SUM2.

, который является первым выходом для блока формирования дальностей начала маневра и начала стрельбы 10, далее D_нм идет на СУ ЛА 12.The sum received at the output of SUM2, multiplying in MU3 with 8 D _y coming from the second output of the comparison unit, forms a signal

, which is the first output for the block forming the ranges of the beginning of the maneuver and the beginning of firing 10, then D _nm goes to the SU 12.

, перемножаясь далее в МУ6 N со значением

, поступает на второй вход СУМ3, где и образуется второй выходной сигнал блока формирования дальностей начала маневра и начала стрельбы 10: дальность начала стрельбы

В элементе сравнения дальности постоянно сравниваются текущая D и вычисленная дальность начала стрельбы D_н, и при выполнении (с некоторой заданной точностью) условия D≤D_н формируется разрешающий сигнал, который далее идет на ПУ 14.In addition, D _{nm is} supplied to the first input of SUM3. The inputs of D1 receive from the PSA the values of the rate of fire of the launcher N (rds / min) and the length of the queue n _Pts (rds). Received signal

further multiplying in MU6 N with the value

, goes to the second input of SUM3, where the second output signal of the unit for forming the ranges of the beginning of the maneuver and the beginning of firing 10 is formed: the firing range

In the range comparison element, the current D and the calculated firing start range D _{n are} constantly compared, and when the condition D≤D _n is fulfilled (with some specified accuracy), an enable signal is generated, which then goes to the control unit 14.

Note. The circuit consists of well-known devices such as a multiplier (MU), adder (SMS), a functional converter (FP), the implementation of which (dialing schemes on elements) are widely given in the relevant literature, for example [7, 8].

.Figure 5 presents a diagram of the formation of a systematic miss SD relative to the OS

.

Here:

AB - line of sight of the target (SD),

C is the point where the projectile meets the target,

K is the predicted meeting point of UR and OS,

,

- скорости соответственно ОС и УР,

,

- speeds respectively OS and UR,

D is the relative range of the OS-UR at the time of the shot,

D _y - anticipated (flight) projectile range,

D _p - the range of the line (between the OS and the target) at the time of the meeting with the goal of the last shell of the queue.

и

, и в общем случае наклонная в с.к. X_нY_нZ_н·cosq=cosβ·cosε.The plane of attack (ΔABK) includes vectors

and

, and in the general case inclined in s.k. X _n Y _n Z _n cosq = cosβ cosε.

при отражении атаки УР со стороны задней полусферы (q=180°) от упрежденной дальности последнего выстрела D_у.6 is a combined schedule: the need for reloading the OS n _OS and OS probability unaffected

when reflecting the attack of the SD from the rear hemisphere (q = 180 °) from the anticipated range of the last shot D _y .

a) for POPs based on two machine guns TKB-764: d = 6 mm, N _∑ = 20,000 rds / min, v ₀ = 1050 m / s, C = 2.88 m ² / kgf, σ _tr = 3.0 mrad;

b) for POPs based on the TKB-776 gun: d = 57 mm, N = 900 rds / min, v ₀ = 500 m / s, C = _1/3 m ² / kgf, σ _tp = 4.0 mrad:

In Fig. 7, the dependences of the probability of survival of the OS on the anticipated range of the last shot D _in a) are plotted when the OS is overloaded after the end of firing n _oc = 0 and 6 units. for POPs based on two 6-mm machine guns TKB-674, σ _t.p. = 3.0 mrad:

b) in case of overload operating after the end of shooting n _oc = 0 and 2 units. for POPs based on the 57-mm gun TKB-776, σ _tr = 4.0 mrad.

On Fig as an example, a sequence diagram of the work of POPs OS.

The cycle diagram illustrates the claimed method of protecting an aircraft from attacking SDs. As can be seen from Fig. 8, in addition to the traditional operations, usually carried out in the following sequence: detection of radar targets and the issuance of target designation (TS) from the survey radar to the radar, capturing the radar target for tracking (in turn, including an overview of the radar in a given sector, working off the control center with the goniometer channel and tracking the target, working out the control center with the rangefinder channel), tracking, calculating in the PSA the angular corrections of firing on two channels and working out them with a power drive - additionally sequentially performed operations were introduced: the choice of the most attack hydrochloric from attacking including identification ur definition of the required slip ^consum h, determination of distances D starts _nm maneuver and D _n the shooting, shooting at CP SD approximation for distance D _n and maneuver at a distance D _nm.

The sequence of execution and approximate durations (execution time) of the above operations, see the sequence diagram of Fig. 8.

The following is an example of a reflection of an attacking UR OS using the proposed method and the OS fire protection system implementing it. The case of a two-stage survey and sighting system (radar + OLS, see figure 3) is considered.

Previously, before the start of a combat operation, the characteristics of a defensive launcher must be entered into the aircraft’s on-board computer system: initial velocity v ₀ , m / s, projectile ballistic coefficient s, m ² / kgf, firing rate N, rds / min, assumed based on the ammunition, length n _och queue rds., and overload OS n _os.

After the appearance of a danger signal issued by the threat warning equipment available on almost every combat aircraft, the search radar 2 is turned on.

When attacking targets are detected, search radar 2 issues a preliminary target designation of OLS 3. In the indicated sector, the radar searches for targets. Next, the target is simultaneously captured by the Goniometric and rangefinder OLS channels and tracking of the target begins: in this case, the angular coordinates of the target β and ε are measured using the sighting device by continuously tracking the target. The angular velocities ω _YD and ω _ZD are measured using gyroscopic sensors installed on the optical sighting station 3.

Since it is necessary to have ≥10 marks from the start of the OLS range finder issuing into the on-board computer system, and the range finder's discrete operation is 4-10 Hz, about 1 second tracking of the range finder is additionally required.

In parallel with the described processes of detecting, issuing and practicing missile defense, escorting before the start of firing, the most attacking target is selected and identified, the miss h ^hr needed for this type of SD is ^determined .

The identification and selection of the most attacking target is widely known and used in modern technology. To one degree or another, these operations are carried out by sighting and navigation systems of almost all combat aircraft. For example, the aiming and navigation system of modern fighters in the discrete direction finding mode (tracking up to 10 targets) records the ranges to the targets and issues them to the onboard counting and solving device, the movement of each target is predicted taking into account the speed of its approach to the aircraft, and the two most attacking targets are automatically identified. If desired, the pilot can make his own adjustments to the selection of these goals. Next, the transition to continuous direction finding (accurate tracking) of the selected target.

Algorithms for identifying and selecting the most attacking targets are presented in more detail in the relevant literature, for example [6].

After taking on target tracking such as UR OLS in the counting-decisive device (SRP) 5, the angular corrections of firing are determined (calculated) through two channels Δβ and Δε. The power drives of the installation 11, working out the control signals Δβ and Δε, at each moment of time unfold the trunks of PU in the right direction.

After determining ^consum h and introducing it into the PSA 5 via additional maneuver shooting range selection device 6 according to the previously determined algorithm obtained 1-4 rational range beginning maneuver and the shooting _nm D _n and D (cm. 3 and 4).

в блоке 9 с использованием информации с ПрНС: β, ε, v_oc и Н и СРП: v₀, с, N, n_оч, вычисляется первое значение t_у, которое, в свою очередь, поступает на управляющие входы блока формирования дальности рубежа 7 и блока сравнения 8. В блоке 7 по управляющим сигналам t_у и D_у (с блока 8) с использованием информации с ПрНС: β, ε и v_oc вычисляется значение D_p, которое поступает на вход блока сравнения 8.Device 6 operates as follows. By the first initial value

in block 9, using information from the PRNS: β, ε, v _oc and H and PSA: v ₀ , s, N, _npt , the first value t _{y is} calculated, which, in turn, is fed to the control inputs of the block forming the range of the boundary 7 and comparison block 8. In block 7, according to the control signals t _y and D _y (from block 8), using the information from the PRS: β, ε, and v _oc , the value of D _{p is} calculated, which is input to the comparison block 8.

, а также задаваемое летчиком, исходя из типа ОС и условий полета, значение n_ос, а с СРП h^потр. В блоке осуществляется сравнение полученного значения h с заданным h^потр. При

идет следующая итерация с шагом по D_y. Цикл повторяется до выполнения условий ε≤ε^треб.At the input of block 8, in addition to the control signals from block 7 D _p and block 9 t _, information from the PRS is additionally received:

And given by the pilot, according to the type and operating flight conditions, the value of n _a, and the PSA h ^consum. In the block, the obtained value of h is compared with the given h ^cons . At

the next iteration is performed in increments of D _y . The cycle is repeated until the conditions ε≤ε ^des.

Methods for solving nonlinear algebraic equations with a given accuracy are widely known, in particular [8].

When the condition ε≤ε ^required, ie, at the end of the iteration process, the signal D _y from the second output of block 8 closes the circuit of block 10, at the output of which we obtain a signal D _nm , and D _n , which enters the OS control system 12, respectively, and the firing signal (for D≤D _n ) - to the third input of PU 14.

As a note, it should be noted that to reduce the number of crucial elements in block 10, when generating a signal, it provides a second option when intermediate signals are used: sinq from the output of the cosine-sine converter (block 7) and cosψ _n from the output of the SUM (block 7) .

A more detailed description of the operation of the device 6 is given earlier.

When approaching the attacking SD at a distance D = D _n UE produces n _och queue length, and after shooting at the distance D = D _nm, corresponding to the last shot, the OS starts to perform intermittent overload maneuver n _oc.

For example, a front-line fighter (FI) equipped with POPs based on two 6-mm machine guns TKB-764 (N _∑ = 20,000 rds / min, v ₀ = 1050 m / s) is attacked by a Sidewinder-type SD from the rear hemisphere ( q = 180 °), v _p = 700 m / s, v _oc = 200 m / s.

According to the table for the SD type «AMRAAM» h = 18 m ^consum. Taking as permissible overload n _oc = 6 pcs., Entering a nomogram (6), from which it follows that FI maneuver should begin at _y = D 180 m. This corresponds to the relative range of the last shot and, accordingly, the starting distance of the maneuver D _n = D _nm = 335 m. Then firing in a half-second burst must begin at a range of D _ns = 335 + 0.5 · 500 = 585 m.

The proposed method and its implementing POPs can use any machine-gun or cannon launcher located on the aircraft, and in the long term - a combat laser installation [9, 10].

The most effective use of the method is to protect the rear hemisphere of light maneuverable carriers, for example, front-line fighters equipped with POPs based on machine guns, since it allows you to solve the problem under tight overall-mass restrictions. For example, POP-based guns TKB-764 mass arms group G will be _nB = 220 kg with a relatively small force action on the support arms (F _dep = 2000 kg) against G _nB = 500-1000 kg and _fin F = 4000-8000 kg for POPs built on the basis of guns.

Using the proposed method and the system that implements it will provide the following advantages over existing ones.

- Increased survival of the aircraft, see Fig.7.

- In addition, it should be noted in addition the reduction in the mass and overall characteristics of the group of defensive machine-gun (cannon) weapons due to the possibility of using the most “weak” type of destruction, which can be provided even by “light” machine-gun installations, as well as the associated reduction in recoil force when firing, in the case of using combat laser systems to protect aircraft, a decrease in their required power, and hence mass and size characteristics and cost.

Information sources

1. V.K. Babich. "Aviation in local wars", M., Military Publishing, 1988, pp. 165-166.

2. V.E. Rudnev. Textbook for the course "The effectiveness of airborne equipment systems for aircraft", M., MAI, 1975, pp. 68-69.

3. News of foreign science and technology. Aircraft weapons systems, No. 11, 1987; pg. 19-21.

4. R. D. Kuzminsky. Guided missile weapons aviation Part I. Air-to-air missiles (lecture notes), M., MAI, 1975.

5. R.V. Mubarakshin, V.M. Baluev, B.V. Voronov. “Aiming firing systems”, part I, M., “VVIA Edition named after prof. N.E. Zhukovsky, 1973, pp. 78-90, 96-97.

6. A.S. Malgin. Fire control of anti-aircraft missile systems M., Military Publishing, 1976.

7. E. D. Gorbatsevich, F. F. Levinson. “Analog modeling of control systems”, M., ed. Science, 1984.

8. E.A. Arkhangelsky, A.A. Znamensky and others. “Modeling on analog computers”, Leningrad, ed. “Energy”, pp. 105-114.

9. A. Demin. A laser halfway to Star Wars, Technology and Arms magazine, No. 3, 2004, pp. 35-40.

10. "The creation of an air-based laser remains a priority project in the United States," ARMS-TASS News Feed, "Aviation, Space, Arms," 12/09/03.

11. I. Smyslov. "Combat lasers are already being tested," Independent Military Review, April 16-22, 2004, No. 14 (374).

Claims (10)

1. A method of protecting aircraft (LA) from guided missiles (SD), including the search, detection and tracking of missiles, determining angular corrections of the weapons of destruction of the missiles to determine its spatial position, the impact on the missiles, taking into account certain amendments, characterized in that up to the beginning of the damaging effect, the means of destruction emit the most attacking of the attacking SDs and determine the required miss of the allocated SD, the range of the start of the maneuver of the aircraft and the range of the impact, while the damaging effect tvie produce at a certain distance, after which on a certain range beginning aircraft maneuver his maneuver performed with a permissible overload upwards in a vertical plane to the SD span. 2. The method of protection according to claim 1, characterized in that the required miss, the range of the start of the maneuver of the aircraft, the range of the damaging effect is determined from the following mathematical relationships:

where h ^spr is the required miss of the most hazardous identified SD, m; D _nm - range of the beginning of the maneuver of the aircraft; D _n - the range of the damaging effect; D _y , D _p - respectively, the anticipated range of the last shot and the range, m; t _y - flight time of the projectile, s; n _OS - permissible aircraft overload, units; v _oc , v _p - speeds, respectively, of the aircraft and SD, m / s; β, ε - target viewing angles in the coordinate system associated with the carrier, rad;

- approach speed of UR and LA, m / s; g is the acceleration of gravity, m / s ² ; K ₁ (K ₂ ) - approximation coefficients t _y (D _y ), m / s (s / m ² ); K _1.2 = K _1.2 (C _H D _y , v ₀₁ ); V ₀₁ , c _H - respectively, the absolute velocity and reduced ballistic coefficient of the projectile, m / s, m ² / kgf; n _Pts - the length of the queue, rds .; N - rate of fire, rds / min. 3. The system of fire protection of the aircraft from the SD, containing a series-connected survey and sighting system, on-board counting device, power drives of the installation, weapons, as well as the navigation system, the outputs of the navigation system are connected to the inputs of the computing device, characterized in that an additional device for selecting maneuver and firing ranges was introduced, which contains a series-connected unit for forming the range of the line, a comparison unit, a unit for forming the maneuver and firing ranges, as well as a flight time formation lock, the first and second inputs of the flight range formation unit are connected respectively to the second and third outputs of the sighting system, the third input of the flight distance formation unit is connected to the first output of the navigation system, its fourth input is connected to the output of the flight time formation unit, and the fifth input of the unit for forming the range of the turn — with the first output of the comparison unit, the first input of which is connected to the first output of the sighting system, to its second and third moves the signals from the setting devices, respectively, the required value of the slip h ^consum and permissible overload LA n _axes, the fourth input of the comparator is connected to the output of the forming flight time, the first and second inputs of the block formation flight time are connected respectively to the second and third outputs observation-sighting system, its third input is connected to the first output of the comparison unit, the fourth and fifth inputs of the flight time formation unit are connected respectively to the first and second outputs of the navigation system we, at its sixth and seventh inputs, receive signals from the adjusters of the ballistic coefficient c and the initial velocity of the projectile, v ₀ , the first input of the maneuvering and firing range formation unit is connected to the first output of the navigation system, its second, third and fourth inputs are connected respectively to the second , the third and first outputs of the survey and sighting system, the fifth, sixth and seventh inputs of the unit for forming ranges of maneuver and firing receive signals from the adjusters, respectively, the rate of fire N, lengths queue n _och and v _p missile speed, ninth its input connected to the output of the forming flight time, and the tenth - a sixth output of the navigation system, the first maneuver and firing output formation unit ranges coupled to an input of aircraft control systems, and its second output - with entrance means of destruction. 4. The fire protection system according to claim 3, characterized in that the block forming the range is made in the form of a series-connected first multiplier, a block for converting the cosine of an angle into a sine, a second multiplier, a block for converting a sine of an angle into cosine, an adder and a third multiplier , as well as series-connected fourth, fifth and sixth multiplier devices, and the first and second inputs of the first multiplier device are connected respectively to the outputs of the first and second of the second blocks for determining the cosine of the angle (cosine converters), and its output is with the second input of the sixth multiplier, the output of the fifth multiplier is connected to the second input of the second multiplier, the output of the sixth multiplier is connected to the inverse second input of the adder, the inputs of the first and second cosine converters connected respectively to the second and third outputs of the sighting system, the first and second inputs of the fourth multiplying device are connected respectively to by the output of the flight time generation unit and the first output of the comparison unit, the first output of the comparison unit is also connected to the second input of the third multiplier device, the second input of the fifth multiplier device is connected to the first output of the navigation system. 5. Fire protection system according to claim 3, characterized in that the comparison unit is made in the form of series-connected first divider, first quadrator, first adder, first multiplier device and extremum search unit, as well as series-connected second adder, second quadrator and second a multiplying device, the first and second inputs of the second adder being connected respectively to the output of the first divider and to the output of the flight time generation unit, and the output of the second multiplying device connected to the second input of the first adder, the first and second inputs of the first divider are connected respectively to the output of the range forming unit and the first output of the sighting system, the second input of the second multiplying device receives a signal from the master of the permissible overload of the aircraft _nos , second and inverse third the inputs of the search block of the extremum of the function are connected respectively with the setter of the initial value of the anticipated range

and with the master of the required miss h ^rub . 6. The fire protection system according to claim 3, characterized in that the flight time formation unit is made in the form of series-connected relative air density formation units, a first multiplier device, a first approximation coefficient formation unit, a divider, and a second, third, and fourth connected in series multipliers, the first adder, the square root extraction unit and the second approximation coefficient formation unit, as well as the first qua a second multiplier device, a second adder, the second input of the first approximation coefficient generation unit being connected to the output of the square root extraction unit, and the first input of the second approximation coefficient generating unit to the output of the first multiplier device, the divider output connected to the input of the second adder, the second input the fifth multiplier device is connected to the output of the second block of the formation of the approximation coefficient, the first and second inputs of the first adder are connected to the outputs ootvetstvenno second and third squarer to the input of the second squarer and a second input of the second multiplier unit is fed a signal from the first output of the navigation system, the input of the third squarer and a first input of the second multiplier unit is fed a signal from setpoint initial velocity v _0, the first input of the fourth multiplier unit is coupled to the output of the sixth multiplying device, the inputs of which are connected to the first and second cosine converters, the inputs of which are connected respectively to the second and third Exit observation-sighting system, forming the input of the relative density of the air unit is connected to the second output of the navigation system, the second input of the first multiplier unit is connected to a setter of the ballistic coefficient, the first input of the first divider and the input squarer connected to the first output of the comparator unit. 7. Fire protection system according to claim 3, characterized in that the unit for forming maneuver and firing ranges is made in the form of series-connected first multiplying devices, a block for converting the cosine of an angle into a sine, a second multiplying device, a first quad, a first adder with an inverse input, a first a square root extraction unit, a second adder, a third multiplier, a third adder, a range comparison element, and a fourth multiplier connected in series, a second quadrator, a fourth adder with an inverse first input, a second square root extraction unit, a fifth multiplier device, as well as sequentially connected firing rate setter N, a first divider and a sixth multiplier device, the first input of the fourth multiplier device being connected to the output of the cosine angle to sine, the second input of the second adder is connected to the output of the fifth multiplier, the second input of the third adder is connected to the output of the sixth multiplier roystva; the second input of the second multiplier device is connected to the output of the seventh multiplier device, the first input of which is connected to the output of the second divider, the first input of which is connected to the second output of the comparison unit, and the second input to the output of the flight time generation unit, the second input of the fifth multiplier is connected to the output the second divider, the second inputs of the fourth and seventh multiplying devices are connected to the first output of the navigation system, the first and second inputs of the first multiplying device are connected s, respectively, the first and second cosine converters whose inputs are connected respectively to the third and second outputs of surveillance-aiming system, the second fourth adder input connected to the output of the third squaring, to the input of which is fed a signal from setpoint v _p missile velocity, the second input of the third multiplier device connected to the second output of the comparator, the second input of the first divider is connected with setpoint _och queue length n, a second input of the sixth multiplier device connected to the first output Panoramic -pritselnoy system, and the second input range comparison element - a sixth output of the navigation system. 8. The fire protection system according to claim 3, characterized in that the unit for forming maneuver and firing ranges is made in the form of series-connected first quad, first multiplier, first adder, square root extraction unit, second multiplier, second adder, third multiplier , the third adder, the range comparison element, as well as the series-connected firing rate setter N, the first divider, the fourth multiplier device, the output of which is connected to a third adder, wherein the inverse second input of the first multiplier is connected to the outputs of the second quadrator, the input of which is connected to the first output of the navigation system, the second input of the first adder is connected to the output of the third quadrator, the input of which is connected to the rocket speed adjuster v _p , the second input of the second multiplier connected to the output of the second divider, the first input of which is connected to the second output of the comparison unit, and the second input of the second divider is connected to the output of the unit of formation of flight time In addition, the input of the first quadrator is connected to the output of the block transforming the cosine of the angle into sine, which, in turn, is included in the block for forming the range of the boundary, and the second input of the second adder is connected to the output of the block transforming the sine of the angle into cosine, which, in turn, is also in block forming the range of the turn, the second input of the third multiplier device is connected to the second output of the comparison unit, the second input of the first divider is connected to the master of the queue length n _och , the second input of the fourth multiplier device is connected with the first output of the survey and sighting system, and the second input of the range comparison element - with the sixth output of the navigation system. 9. The fire protection system according to claim 3, characterized in that the means of destruction is a machine-gun (cannon mount). 10. The fire protection system according to claim 3, characterized in that the means of destruction is a combat laser installation.

Images