RU2436030C1 - Guided missile control method - Google Patents

Abstract

FIELD: weapons and ammunition.

SUBSTANCE: method involves formation of independent stabilised sighting line and its alignment with target, deviation of gun barrel from sighting line through sighting and lateral lead angles, firing, capture of guided missile with guidance system, measurement of deviations of missile from sighting line, formation and transmission to it of control commands corresponding to these deviations, generation and supply to missile control members of the signals corresponding to these commands. If several targets are available, their coordinates are measured, stored and entered to the field of vision. In case of missing the first (closest) target and at fulfillment of conditions ψ_2,1<{[(D₂-D₁)/V_m]-t_l}ω_nh, φ_2,1<{[(D₂-D₁)/V_m]-t_l}ω_nv, where D₁ - distance to the first (closest) target; D₂ - distance to the second target; V_m - cruise speed of controlled missile; t_l - time losses determined with response time of guidance system and operator; ω_gh, ω_nv - rational angular guidance speeds of controlled missile in horizontal and vertical planes respectively; ψ_2,1, φ_2,1 - angular discrepancies between the second and the first lines of targets in horizontal and vertical planes; movement of sighting line is performed from the first target to the second target, and then in case of bad shots to farther located targets till the target is hit or control cycle is completed.

EFFECT: increasing firing control efficiency of guided missile.

Description

The proposed method of guiding a guided missile relates to the field of command and control of military facilities, and more specifically to the management of automated weapons systems mounted on tanks, infantry fighting vehicles, armored personnel carriers, and others containing missile and artillery weapons. Such control methods provide automation of 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 fired missile, 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 inclusion unit and weapon stabilizer, which ensures a relatively high efficiency of these systems.

However, 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 ammunition 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, p.10-14), deflecting guided missiles (SD) in flight from the aiming point.

There is also a known method of controlling firing from a guided missile gun, including the formation and alignment of an independent stabilized aiming line, 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 fired missile, and firing a shot.

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 corrections block, 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 during firing, with the exception of corrections for the action of air currents and dust interference when firing guided missiles.

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. Guided missile shooting 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 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 time the guided missile flies to the target, and makes it difficult to observe the target. Moreover, the presence of a dust cloud and inept operator actions can prevent the guidance system from capturing a guided missile and lead to its loss. The technical characteristics of modern guided missile guidance systems provide for the capture of a guided missile and its subsequent guidance in the presence of a dust cloud. However, 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 longer the time for combining the aiming line and the target. 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 occurs much more slowly, due to which the gunners in some cases lose their target, and therefore the missile.

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 the instruments 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 guided missile gun and eliminate the above disadvantages.

The solution to this problem is achieved by the fact that in the guided missile guidance method, including the formation of an independent stabilized aiming line and combining it with the target, 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 fired missile, firing a shot, capturing a guided missile by a guidance system, measuring through a guidance system deviations of a guided missile from the aiming line in p the process of its flight, the automatic generation and transmission to it of control commands corresponding to these deviations, the automatic generation and transmission to the missile control organs of signals corresponding to these commands, in addition to several targets, their coordinates, including the range, are measured, stored and entered into the field of view, azimuthal angle and elevation angle of the target, and in case of a miss on the first in range (near) target and the fulfillment of the conditions

ψ _2,1 <{[(D ₂ -D ₁ ) / V _p ] -t _p } ω _ng ,

φ _2.1 <{[(D ₂ -D ₁ ) / V _p ] -t _n } ω _nv ,

where D ₁ - range to the first (near) range of the target,

D ₂ - range to the second target range,

V _p - marching speed of the guided missile,

t _p - time loss, determined by the inertia of the guidance system and the operator,

ω _ng , ω _nv are the radial (disposable) angular guidance speeds of the guided missile in the horizontal and vertical planes, respectively

ψ _2,1 , φ _2,1 - angular mismatches between the second and first lines of targets, respectively, in the horizontal and vertical planes,

moving the aiming line from the first to the second target. and then during misses and on the targets that are further in range (3rd, 4th, etc.) until the control cycle hits or ends.

The introduction of new features allows you to obtain new information about the shooting conditions (about the presence of other targets, the value of their coordinates, etc.) and adjust the fire control, which ensures an increase in its effectiveness by creating the possibility of firing a single missile sequentially at several targets in case of loss or miss.

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 targets, determines the type of ammunition (guided missiles) for their 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 sequentially combines the aiming mark (independent stabilized aiming line) of the sight with the controls on the control panel and presses the range measurement button. In this case, the laser range finder is triggered and information about the range to the corresponding target D _{c is} fed to the inputs of the ballistic computer and in the gunner’s field of view. At the same time, information on the azimuthal angles and elevation angles of the target of the corresponding targets is measured, stored and fed into the calculator and field of view.

The formation of a dust cloud can significantly affect 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 effect of longitudinal or transverse wind, etc.). Therefore, the algorithm of actions of the gunner in some cases must be clarified in accordance with the dynamics of changes in the shooting conditions.

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 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 is then fed to the summing unit and guidance drives of the guns and turrets, respectively.

At the same time, the angular dimensions and speed of movement of the dust cloud formed during firing are visually determined, and the target’s screening time is approximately determined.

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’s contour and the duration of the screening of the target with a dust cloud are compared among themselves. If the value of the first exceeds the value of the second, which indicates that the screening of the target will stop before the rocket approaches it, the gun barrel is deflected before the shot is fired towards the lateral movement of the dust cloud by an additional angle.

However, the deviation of the gun barrel towards the lateral movement of the dust cloud can lead to both a reduction in the effects of dust interference, that is, to increased firing efficiency, and to the loss of guided missiles and the possibility of firing at the second target.

In the event of a miss or loss of a target, information about what is fed into the gunner’s field of view and the presence of several targets, the coordinates of which, including the range, azimuth angle and elevation angle of the target, were previously measured, stored and entered into the field of view, as well as the fulfillment of

ψ _2,1 <{[(D ₂ -D ₁ ) / V _p ] -t _p } ω _ng ,

φ _2.1 <{[(D ₂ -D ₁ ) / V _p ] -t _n } ω _nv ,

where D ₁ - range to the first in range (near) target (m),

D ₂ - range to the second target range (m),

V _p - marching speed of the guided missile (m / s),

t _p - time loss determined by the inertia of the guidance system and the operator (s),

ω _ng , ω _nv - rational (disposable) angular velocity of guided missile guidance in the horizontal and vertical planes, respectively (rad / s),

ψ _2,1 , φ _2,1 - angular mismatches between the second and first lines of targets, respectively, in the horizontal and vertical planes (rad),

move the aiming line from the first to the second in range target, and then with misses and subsequent in range of the target (3rd, 4th, etc.) until it hits or ends the control cycle. Moreover, the numbering of parameters in the expressions for ψ and φ will change in accordance with the numbering of goals.

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

Claims (1)

The guided missile guidance method, including the formation of an independent stabilized aiming line and its alignment with the target, 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 fired missile, firing a shot, guided missile capture by the guidance system , measurement by means of a guidance system for deviations of a guided missile from the aiming line during its flight, automatic formation the transmission and transmission to it of control commands corresponding to these deviations, the automatic generation and transmission to the missile control organs of signals corresponding to these commands, characterized in that when there are several targets, their coordinates, including range, azimuth angle, are measured, entered into the field of view and the elevation angle of the target, and in case of a miss on the first in range (near) target and the fulfillment of the conditions
ψ _2,1 <{[(D ₂ -D ₁ ) / V _p ] -t _p } ω _ng ,
φ _2.1 <{[(D ₂ -D ₁ ) / V _p ] -t _n } ω _nv ,
where D ₁ - range to the first (near) range of the target;
D ₂ - range to the second target range;
V _p - marching speed of the guided missile;
t _p - time loss, determined by the inertia of the guidance system and the operator;
ω _ng , ω _nv — rational (disposable) angular guidance speeds of the guided missile in the horizontal and vertical planes, respectively;
ψ _2,1 , φ _2,1 - angular mismatches between the second and first lines of targets, respectively, in the horizontal and vertical planes,
they move the aiming line from the first to the second target, and then with misses and to subsequent targets in range (3rd, 4th, etc.) until the control cycle hits or ends.