RU2345310C1 - Method of guided shell or missile fire control - Google Patents

Abstract

FIELD: weaponry.

SUBSTANCE: invention relates to fire control methods. The proposed method comprises the generation of an independent aiming line and aligning it with the target, moving the gun barrel from the said aiming line for the aiming angles and cross-track lead defined depending upon the fir conditions and shell or missile ballistic characteristics. On launching a guided shell, additionally will be defined the lengthwise wind direction and speed, qualification of the operator, optimum time of guiding the guided shell into the target area edges, the lateral angular sizes and speed of dust-fume cloud formed in firing, the time of shielding the target by the aforesaid cloud, the aforesaid values being compared between themselves. If the first value exceeds the second one, prior to shooting, the gun barrel is moved towards the dust-fume cloud side motion by an additional angle.

EFFECT: increase of guided shell fore control efficiency by some 5 to 10 %, while in mountain-deserted areas with greater dust-fume shields the efficiency increases by more than 15%.

Description

The proposed method of firing control relates to the field of control of military facilities, and more specifically to the management of automated weapon systems installed on tanks, infantry fighting vehicles, armored personnel carriers, etc., containing missile and artillery weapons. Such control methods provide automation of the processes of accounting for shooting conditions, determination of aiming angles and lateral lead, as well as the introduction of amendments to the position of weapons at the time of the shot.

A known method of controlling fire, including the formation and alignment with the goal of a dependent aiming line, deviation of the gun barrel from the aiming line at the aiming angles and lateral lead, determined depending on the shooting conditions and ballistic characteristics of the projectile or missile being shot, and firing. This method is implemented in automated weapons control systems (ASUV) of the tanks of the first post-war generation T-55 and T-62 (see, for example, "Manual on the material part and operation of the T-55 tank. Military Publishing, M., 1965) , each of which contains a control panel, automated gun guidance drives in the vertical and horizontal planes with their power-on unit and weapon stabilizer, which ensures a relatively high efficiency of these systems.

However, this method is characterized by disadvantages. Alignment with the target of the dependent aiming line associated with armament leads to the fact that the tracking errors for the target are determined by disturbances acting on the armament, which are large (in the horizontal plane they reach 2 etc. when shooting on the move). In addition, when shooting in desert, mountain-desert and coastal areas, the accuracy of shooting with all types of shells can additionally (up to 1 etc. or more) change. This is because in these areas, due to the high heating temperature (up to 60 ° C) of the underlying surface, powerful air currents arise above it (see, for example, Savkin LS, Lebedev BD Meteorology and artillery firing. M. , Military Publishing House, 1974, pp. 10-14), deflecting projectiles in flight from the aiming point.

It should also be noted that the measurement of the range in these ASUVs to the target is carried out using rangefinder scales, which leads to a large error (more than 10%) of its measurement, and therefore the error in determining the aiming angle. Therefore, when shooting from T-55 and T-62 tanks, the probability of hitting, as a rule, does not exceed 50%, and the effective fire range is only 1400-1600 m.

There is also a method of controlling the firing of a cannon with a guided projectile or guided missile, including the formation and alignment with the aim of an independent aiming line, the deviation of the gun barrel from the aiming line at the aiming angles and lateral lead, determined depending on the firing conditions and ballistic characteristics of the projectile or missile being shot, and shot production.

This method is implemented in the automatic control system of the T-80B tank (see, for example, the T-80B tank. TO and IE. Book 1. M., Military Publishing House, 1984, pp. 46-95). In technical essence and essential features, it is the closest to the claimed and adopted for its prototype. ASUV of the T-80B tank contains a serially connected control panel, sight, summing unit and gun guidance drive, ballistic computer, manual correction unit, the outputs of which are connected to the corresponding inputs of the ballistic computer by the number of corrections, the ballistic sensor of the fired munition, a laser range finder and a wind sensor, the output of each of which is connected to the corresponding inputs of the ballistic computer.

The effectiveness of the method implemented by this ASUV, compared with the previous one, has significantly increased. The effective fire range increased to 2200-2500 m, which was achieved primarily due to the implementation of an independent aiming line, which allowed to reduce tracking errors by 3-5 times, and automatic input of the main corrections to the aiming angles and lateral lead. The introduced elements made it possible to take into account a number of corrections when firing, with the exception of amendments for the action of longitudinal wind and dust interference when firing guided projectiles.

According to the experience of military operations in Afghanistan and Chechnya, due to the action of powerful air currents that are characteristic of mountainous and desert regions, significant dusty interference arises, increasing during firing. Shooting with guided projectiles (missiles) is characterized by a long (more than 12 seconds when firing at maximum range) retention of the sighting line on the target. When launching guided projectiles (missiles) through the gun’s barrel in the field of view of the gunner’s sight, as a rule, a dust cloud arises (especially on dusty soils), the dispersion time of which is in some cases commensurate with the flight time of the guided projectile (missile) to the target, which makes observation difficult for the goal. Moreover, the presence of a dust cloud and inept operator actions can prevent the guidance system from capturing a guided projectile (missile) and lead to its (her) loss. Technical characteristics of modern guided missile guidance systems (missiles) provide capture of a guided missile (missile) and its subsequent guidance in the presence of a dust cloud. The limiting factor in this situation is the lack of visibility of the target by the operator for some time after the shot, which increases its tension due to the uncertainty of information about the position of the target. With the increase in the time the target is not visible, the tension also increases: the lower the qualification of the operator, the more time is needed to combine the aiming line and the target. The ratio of the mathematical expectations of the time (subsequent to the appearance of the target) of combining the aiming line and the target in a series of experiments for operators of the 3rd and 2nd classes, respectively, was 1.3: 1. A close ratio between operators of the second and first classes is 1.1: 1. The situation is aggravated when firing from a place when shooting objects are on the defensive, in trenches, etc., since under these conditions the dispersion of the dust cloud is much slower.

A series of experiments aimed at assessing the influence of dust formation on firing in defense and determining ways to combat it showed:

- firing from a tank located in the trench is seriously complicated due to the low line of fire (20-50 cm above ground level) and the formation of a dust cloud during firing, which impedes observation of the target and the results of the shot;

- when the tank is in the trench, the dust cloud formed when firing from its own gun is so thick that it does not allow to observe the results of the shot through observation devices (including thermal imaging), makes it difficult to track the target and adjust the fire, increases the time to hit the target, and most importantly reduces the likelihood of defeating enemy targets;

- when conducting intense fire from the trench, the air pollution both around and inside the tank increases, which negatively affects the condition of the crew (especially the tank commander), reduces its moral and psychological qualities and can cause the crew to fail;

- the operation of devices and units of the fighting compartment of the tank during the battle requires a large expenditure of electricity, which cannot be provided for a long time by batteries, which in turn requires constant engine operation and further increases the degree of smoke in the field of view of operators.

The objective of the present invention is to increase the efficiency of the method of controlling firing from a gun with a guided projectile or guided missile and eliminating the above disadvantages.

This goal is achieved by the fact that in the method of controlling firing from a cannon with a guided projectile or guided missile, which includes forming and combining with an independent aiming line, deviation of the gun barrel from the aiming line at the aiming angles and lateral lead, determined depending on the shooting conditions and ballistic characteristics fired projectile or rocket, and firing, additionally determine the direction and measure the longitudinal wind speed, calculate the optimal time in ode guided projectile or missile into the circuit controlled with the target longitudinal wind action in accordance with the expression

T _o = [D _c -K _o (L _a ± L _pv )] / V _o ,

where T _about - the optimal time to enter a guided projectile or guided missile into the target circuit,

D _c - the distance to the target,

To _about - an indicator equal to 1, 1.1 or 1.3, depending on the qualifications of the operator,

L _a - the length of the active zone at the target, in which the guided projectile or guided missile is in the contour of the target,

L _PV - the increment of the length of the active zone due to the action of a longitudinal wind,

V _o - flight speed of a guided projectile or guided missile, measure the lateral angular dimensions and speed of movement relative to the aiming line of the dust cloud formed during firing, based on which the duration of the target’s screening is determined in accordance with the expression

T _e = (Ψ _PDO -Ψ _nn) / Ψ _'PDO

where T _e - the duration of the screening of the target with a dust cloud,

Ψ _PDO - lateral angular size of the dust cloud,

Ψ _lp - lateral angular position of the line of sight,

Ψ ' _PDO - lateral angular velocity of the dust cloud,

comparing the values of the optimal time for the introduction of a guided projectile or guided missile into the target’s contour and the duration of shielding of the target with a dust cloud between themselves, and if the value of the first exceeds the value of the second in accordance with

T _o > T _e

before the shot is fired, the gun barrel is deflected towards the lateral movement of the dust cloud by an additional angle in accordance with the expression

ΔΨ≤Ψ _s cosφ ± Ψ _bu ,

where ΔΨ is the additional angle of lateral deviation of the gun barrel,

Ψ _s is the angle of maximum lateral capture by the guidance system of a guided projectile or guided missile,

φ is the angle of aim,

Ψ _bu - lateral lead angle,

the signs "+" or "-" are set respectively for a versatile or one-sided deviation from the aiming line of the additional angle and the angle of lateral lead.

The introduction of new features allows you to obtain new information about the firing conditions (crosswind, the size and speed of the dust cloud, etc.) and adjust the firing control, which improves its effectiveness by clarifying the installation of the lateral lead angle for the various types of ammunition and firing conditions, which leads to a reduction in the duration of dust interference.

The implementation of the method is as follows. Knowing the deviation of the firing conditions from the tabular, enter their value through the regular block of manual corrections to the ballistic computer manually:

- to change the temperature of the charge,

- to change the air temperature,

- change in atmospheric pressure,

- the wear of the bore.

Meanwhile, the operator, observing the battlefield through the sight, detects the target, determines the type of ammunition for its destruction and sets the ballistic sensor in the appropriate position, information about which is fed to the inputs of the ballistic computer. Then the operator combines the aim with the aim using the controls on the control panel of the sighting mark (independent aiming line) of the sight and presses the range measurement button. When this is triggered by a laser range finder and information about the distance to the target D _C enters the inputs of the ballistic computer and other input units that implement the algorithm

T _o = [D _c -K _o (L _a ± L _pv )] / V _o , (1)

where T _o - the optimal time of entry of a guided projectile or guided missile into the target circuit,

D _c - the distance to the target,

To _about - an indicator equal to 1, 1.1 or 1.3, depending on the qualifications of the operator,

L _a - the length of the active zone at the target, in which the guided projectile or guided missile is in the contour of the target,

L _PV ^{- the} increment of the length of the active zone due to the action of a longitudinal wind,

V _about - the flight speed of a guided projectile or rocket.

In the expression (1), the qualification index of the operator K _о as applied to the armament complex of the prototype corresponds to classes 1, 2 and 3.

The correction L _pv for the increment of the length of the active zone at the target due to the action of the longitudinal wind is taken with the “+” sign in the headwind and with the “-” sign in the tailwind.

When firing a guided projectile (guided missile) in a mode with excess and in the absence of dust interference, the length of the active zone of the target at which the guided projectile is in its circuit L _a is determined by the moment the guided projectile falls from the elevation path (3-5 m above the aiming line ) and its entry into the contour of the target (reduction to the line of sight). In the prototype L _a = 600-800 m and provided T _o optimality, since for automatic systems by virtue of their known characteristics tend to meet the requirement _of ensuring optimality T to precisely rocket "vstrelivalas" into the core at the purpose that when ceteris paribus increases the likelihood of a hit.

However, the formation of a dust cloud can significantly change the situation. Due to the long time of shielding the target with a dust cloud, the optimality of the time it takes for a guided projectile to enter the target loop may be impaired (including due to the low skill of the operator, the action of a longitudinal wind, etc.). Therefore, the algorithm for determining T _about must be refined in accordance with the expression (1).

Next, the operator (gunner) performs loading the guns by pressing the “MZ” loading mechanism button, while the standard wind sensor is triggered, and information about the side wind speed in the area of the firing position of the weapon complex (tank, infantry fighting vehicle, armored personnel carrier, etc.) and other conditions firing and indicators enters a full-time ballistic computer and an additional calculating and deciding device, where it is converted according to well-known algorithms (see, for example, “Fundamentals of automation and tank automatic systems.” M., VABTV, 1976, p. 508-519) corresponding e angles of aiming (elevation) and lateral lead for given firing conditions, which are then fed to the summing unit and guidance drives of the guns and turrets, respectively.

At the same time, the units are included in the operation, with the help of which the lateral angular dimensions and the speed of movement of the dust cloud formed during the shot are measured, the time of shielding the target by it is determined in accordance with the expression

T _e = (Ψ _PDO -Ψ _nn) / Ψ _'PDO

where T _e - the screening time of the target with a dust cloud,

Ψ _PDO - lateral angular size of the dust cloud,

Ψ _lp - lateral angular position of the line of sight,

Ψ ' _PDO - lateral angular velocity of the dust cloud.

As the lateral angular size of the dust cloud, take the lateral deviation of its edge, which is opposite to the direction of motion of the dust cloud. Information on the speed of movement of the dust cloud, as well as on the direction and speed of the longitudinal wind can be obtained on the basis of data contained in meteorological bulletins (see, for example, Savkin L.S., Lebedev B.D. Meteorology and artillery shooting. M. , Military Publishing House, 1974, p.129-142.). The same information can be obtained more quickly on the basis of direct measurement of the lateral angular velocity of movement of the same edge of the dust cloud relative to the scale of the side corrections of the sight (see, for example, the T-80B tank. TO and IE. Book 1. M., Military Publishing House, 1984, p. 59-63, fig. 19 and 20).

The values of the optimal time for the introduction of a guided projectile (missile) into the target circuit and the duration of the target screening with a dust cloud are compared. If the value of the first exceeds the value of the second, which indicates that the screening of the target will stop before the shell approaches it, the gun barrel is deflected before the shot is fired towards the lateral movement of the dust cloud by an additional angle in accordance with the expression

ΔΨ≤Ψ _s cosφ ± Ψ _bu ,

where ΔΨ is the additional angle of lateral deviation of the gun barrel,

Ψ _s is the angle of maximum lateral capture by the guidance system of a guided projectile,

φ is the angle of aim,

Ψ _bu - lateral lead angle,

“+” Or “-” is set, respectively, with a versatile or one-sided deviation from the aiming line of the additional angle and the angle of lateral lead.

Deviation of the gun barrel in the direction of lateral movement of the dust cloud leads to a decrease in the action of dust interference, that is, to an increase in firing efficiency.

The introduction of new features provides an increase in the efficiency of firing with guided projectiles (missiles) under the conditions of dust interference by 5-10%, and when firing in a mountainous-desert area with powerful dust interference, the firing efficiency increases by more than 15%.

Claims (1)

A method of controlling firing from a cannon with a guided projectile or guided missile, including forming and aligning for an independent aiming line, deviating the gun barrel from the aiming line at the aiming angles and lateral lead, determined depending on the firing conditions and ballistic characteristics of the projectile or missile being fired, and production shots, characterized in that they additionally determine the direction and measure the longitudinal wind speed, calculate the optimal input time a guided missile or projectile in the target circuit with the longitudinal wind action in accordance with a mathematical expression

,
where T _o is the optimal time to enter a guided projectile or guided missile into the target’s circuit, s;
D _c - range to the target, m;
K _o - an indicator equal to 1, 1.1 or 1.3, depending on the skill of the operator (dimensionless);
L _a is the length of the active zone at the target in which the guided projectile or guided missile is in the target’s contour, m;
L _pv - increment of the length of the active zone due to the action of a longitudinal wind, m;
V _about - the flight speed of a guided projectile or guided missile, m / s,
measure lateral angular dimensions and speed of movement relative to the aiming line of the dust cloud formed during firing, on the basis of which the duration of the target’s screening is determined in accordance with the mathematical expression:
T _e = (Ψ _PDO -Ψ _nn) / Ψ _'PDO
where T _e - the duration of the screening of the target with a dust cloud, s;
ψ _pdo - lateral angular size of the dust cloud, rad;
ψ _lp - lateral angular position of the aiming line, rad;
ψ ' _PDO - lateral angular velocity of the dust cloud, rad / s,
comparing the values of the optimal time for the introduction of a guided projectile or guided missile into the target’s contour and the duration of shielding the target with a dust cloud between each other and if the value of the first exceeds the value of the second in accordance with
T _o > T _e
before the shot is fired, the gun barrel is deflected towards the lateral movement of the dust cloud by an additional angle in accordance with the mathematical expression:
ΔΨ≤Ψ _s cosφ ± Ψ _bu ,
where Δψ is the additional angle of lateral deviation of the gun barrel, rad;
ψ _z — angle of maximum lateral capture by the guided projectile guidance system, rad;
φ is the angle of aim, rad;
ψ _bu - lateral lead angle, glad
the signs "+" or "-" are set respectively for a versatile or one-sided deviation from the aiming line of the additional angle and the angle of lateral lead.