RU2421681C1 - Guidance system of controlled missiles - Google Patents

Abstract

FIELD: weapons and ammunition.

SUBSTANCE: proposed device includes adder connected between generation unit of control signals and generation unit of control commands, in-series connected switch the input of which is connected to the second output of coordinator, air flow velocity sensor kinematically connected to start-up unit, squaring device, scaling unit and inverter the output of which is connected to the second input of adder, as well as stabilisation unit of trajectory of controlled missile, the input of which is connected to the third output of coordinator, and output is connected to the third input of adder.

EFFECT: increasing the probability of hitting during firing in the described conditions by using the proposed guidance system.

1 dwg

Description

The invention relates to military equipment, and more particularly to guidance systems for guided missiles.

Such guidance systems allow you to hit armored and other enemy targets located on land, water or air. They form the basis of anti-tank and anti-aircraft missile systems, a feature of which is the high probability of hitting enemy targets. The guidance system provides a high probability of hit by guided missiles at ranges significantly exceeding the effective range of firing from a weapon.

Known manual guidance systems for guided missiles (see, for example, A.N. Latukhin's book "Anti-tank weapons", Military Publishing House, Ministry of Defense of the USSR, M., 1974, pp. 192-218). They contain a control drive, a launcher, a sight, control signal and command generating units, a command transmission line, the output of which is connected to guided missile control equipment.

Such guidance systems have disadvantages. The cruising speed of the guided missile does not exceed 80-100 m / s, which leads to a long flight time (20-25 sec), low rate of fire, the presence of an unaffected zone in front of the firing position with a depth of 300-600 m. In addition, training personnel in shooting rules and practical skills are too expensive and complicated, since manual control requires rigorous selection and careful training of operators.

The guided missile guidance system is also known (see, for example, A.N. Latukhin. “Anti-tank weapons.” Military Publishing House, Ministry of Defense of the USSR, M., 1974, p. 208-235). This system, by its technical nature and essential features, is the closest to the claimed one and is taken as its prototype. At the same time, it is the basic object of the proposed system and contains: a control drive, a launcher and a sight, the inputs of which are connected to the output of the control drive, as well as a coordinated missile coordinator whose input is optically coupled to the sight field of view, a control signal generation unit, and a generation unit control teams, the output of which through the command line is connected to the guided missile control equipment.

The effectiveness of this guidance system compared with the previous one has increased significantly. The non-affected area in front of the launcher decreased, the cruising speed of the rocket increased, and, most importantly, the functions of the gunner-operator were simplified by introducing the coordinator into the guidance system (its functions are reduced only to combining the aiming line with the direction to the target, and control commands are generated and transmitted automatically, which increases the accuracy of shooting and minimizes the impact on its results of individual data of the gunner-operator), thereby facilitating the selection of operators, simplified The process was ongoing and the cost of training decreased.

However, this system also has disadvantages. Despite the input of the coordinator and the exclusion of the human operator from the rocket control loop, when the rocket is exposed to external disturbances, for example, the force of the transverse (vertical and horizontal) wind, etc., the guidance occurs with errors, which significantly reduces its accuracy. Compensation of the shear wind neither in modern nor in perspective guidance systems is provided. At the same time, it is known that on flat and desert terrain the accuracy of firing by all types of shells (including guided missiles) can vary significantly. This is because in these areas there are powerful air currents that deflect a guided missile in flight in height and direction from the aiming point. This deviation can be determined by the expression (see, for example, F.K. Neupokoev "Anti-aircraft missile shooting", M., Military Publishing, 1970, p.200-202):

where a cosθ is the normal to the trajectory component of the acceleration of the air flow force,

k _o - gain of the open loop control.

As a result of the action of air currents, the deflection of the rocket can be significant, and the probability of getting reduced by 10-15%.

The aim of the present invention is to increase the efficiency of firing guided missiles by increasing the accuracy of their guidance on the target.

This goal is achieved by the fact that in the guidance system of guided missiles containing a control drive, a launcher and a sight, the inputs of which are connected to the output of the control drive, and the coordinator of the guided missile, the input of which is optically coupled to the sight field of vision, is connected in series, a control signal generating unit and control command generation unit, the output of which through the command transmission line is connected to guided missile control equipment, an adder is inserted, connected between the control generation unit x signals and a control command generating unit, a key in series with an input connected to the second output of the coordinator, an air velocity sensor kinematically connected to the launcher, a quadrator, a scaling unit and an inverter, the output of which is connected to the second input of the adder, as well as a stabilization unit trajectory of a guided missile, the input of which is connected to the third output of the coordinator, and the output to the third input of the adder.

The introduction of new elements and relationships allows us to obtain new information about the firing conditions (air flow rate), to determine and introduce the necessary compensating corrections, which ensures an increase in the accuracy of guided missile guidance.

The proposed technical solution is illustrated by the drawing, which shows the relative position and relationships of the elements of the proposed guided missile guidance system and the following notation is accepted (the proposed elements and communications are shown in dashed lines, and the solid lines are the prototype elements and communications):

1 - target (C),

2 - control drive (PU),

3 - sight (D),

4 - guided missile (UR),

5 - launcher (launcher),

6 - command transmission line (LPC),

7 - coordinator (K),

8 - block generating control signals (BVS),

9 - adder ("+"),

10 - block development of control teams (BVK),

11 - key (C),

12 - block stabilization of the trajectory of a guided missile (BST),

13 - air flow rate sensor (DVP),

14 - quadrator (KB),

15 - scaling unit (MB),

16 - inverter (Iv).

Blocks 1-10 are regular blocks of the prototype and perform the same functions.

The key 11 provides for the inclusion of an air flow rate sensor 13, which usually consists of an impeller, the rotational speed of which is proportional to the speed of the air flow, and a converter for rotating the impeller into an electric signal (see, for example, V.V. Korneev et al. “Fundamentals of automation and tank automatic systems ”, Moscow, VA BTV, 1976, p. 159-161). Block 13 is kinematically connected with the launcher 5 so that the measuring axis of the device is perpendicular to the flight path of the guided missile. The stabilization unit trajectory of the guided missile 12 provides a reduction in the oscillation of the guided missile relative to the average value of its trajectory. It contains a resolution block, triggered by a significant increase in the signal at the output of block 7, and a block for generating an additional correction signal (not shown). The quadrator 14 ensures that the signal supplied to it from the block 13 (i.e., the air flow velocity) is raised to the second power and is fed to the input of the block 15. The scaling block 15 provides a signal corresponding to the aerodynamic force acting on the guided missile as a result of the action of the air flow. Its value is determined by the expression (see, for example, Neupokoev F.K. “Shooting anti-aircraft missiles.” M., Military Publishing House, 1970, pp. 99-121):

where k is the proportionality coefficient that determines the signal level at the output of block 15 from the effective force,

c _y - drag coefficient of the guided missile to the air flow in the transverse plane,

ρ is the density of air,

s is the characteristic area of the guided missile.

The inverter 16 provides a change in the polarity of the signal from block 15.

The proposed guided missile guidance system works as follows.

Using the control drive 2, combining the sighting mark of the sight 3 with the aim of 1 and setting the appropriate position of the launcher 5 with the guided missile 4, the gunner-operator launches the guided missile 4. After the launch, the guided missile 4 enters the field of view of the sight 3 and the field aligned with it view of the coordinator 7. The coordinator provides a signal corresponding to the deviation of the guided missile from the line of sight, and feeds it to the input of the control signal generation block 8, which amplifies and corrects at the control signal and feeds it through the adder 9 to the control command generation unit 10, where it is converted, encrypted, and transmitted as a control command through the command transmission line 6 to the guided missile control equipment 4, which, under the action of the received command, moves to the aiming line, which the mismatch between it and the aiming line is eliminated.

When shooting in the conditions of plains, steppes, deserts, etc., block 11 is turned on (if there is a signal at the second output of coordinator 7) and block 13 (air flow velocity sensor) starts to work, which generates a signal proportional to the air flow velocity V _B. In block 14, this signal is raised to the second power V _B ² , and in block 15 it is finally converted in accordance with expression (1), inverted in block 16, and then fed to the second input of adder 9 as a signal for compensating the air flow force. In adder 9, the compensation signal corrects the control signal in accordance with external disturbances acting on the guided missile caused by air currents. In case of sharp gusts of wind, or at maximum control distances, when the deviations of the guided missile from the aiming line and the signal level at the output of the coordinator 7 become excessive, the resolution block of block 12 is triggered, due to which the additional correction signal is generated by the additional correction signal block (in block 12) , which is fed to the third input of the adder and provides an additional increase in the control signal.

The introduced set of features provides the measurement of external harmful disturbance - air flow velocity, the determination and formation of the necessary compensating correction, which reduces (up to elimination) the deviation of the guided missile from the aiming line, which increases the accuracy of its guidance.

It is established that the probability of hitting during shooting under the considered conditions using the proposed guidance system increases by 10-15%.

In addition, it should be noted that the introduced elements are produced in series and are widely used both in the national economy and in military equipment, which will contribute to the implementation of the proposed system.

Claims (1)

Guided missile guidance system comprising a control drive, a launcher and a sight, the inputs of which are connected to the output of the control drive, and a coordinated missile coordinator whose input is optically coupled to the sight field of view, a control signal generating unit and control command generating unit, the output of which through a command transmission line it is connected to guided missile control equipment, characterized in that an adder is inserted in it, which is connected between the control signal generation unit s and a control command generation unit, a key in series with an input connected to the second output of the coordinator, an air velocity sensor kinematically connected to the launcher, a quadrator, a scaling unit and an inverter, the output of which is connected to the second input of the adder, as well as a path stabilization unit guided missile, the input of which is connected to the third output of the coordinator, and the output to the third input of the adder.

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