RU2165589C1 - Method for fire by artillery guided missile - Google Patents

Abstract

FIELD: armament, in particular, artillery guided missiles with a laser homing head. SUBSTANCE: in the known method consisting in time setting of actuation of on-board systems of guided missile the entire range of firing ranges is divided into separate sections. The respective code is assigned to each section, time intervals for actuation of the missile on-board systems are formed for each section, which are then inserted in the read-only memory. Prior to firing, a code corresponding to the selected section of firing ranges is set, in accordance with which in the process of flight the time intervals for actuation of the artillery missile on-board control systems are read out from the read-only memory. EFFECT: enhanced accuracy of actuation of the missile on-board systems. 1 dwg

Description

 The invention relates to weapons, in particular to artillery guided projectiles with a laser homing head.

 A known method of firing a guided projectile [1], in which before firing using a clockwork set the time of the onboard pyrotechnic thermal battery and the time of sizing of the inertial gyroscope.

 Using an inertial gyroscope, the mismatch angle is measured between the longitudinal axis of the projectile and the stored position at the time of sizing, and the measured angle is compared with the predetermined value of the mismatch angle. Then, at the moment of comparing the measured angle and the predetermined angle, a command is formed to open the rudders and to activate the batteries of the homing head, separate the nose unit and generate a signal to unlock the homing head.

 The disadvantage of this method is the low accuracy of the onboard elements of the projectile, which is caused by the following factors.

The rate of change of the bearing angle, depending on the trajectory, can vary from 1 to 3 ^o / s.

In addition, the bearing angle depends on the amplitude of the oscillations of the projectile at the angles of attack, which reach a value of 10 ^o . All this leads to large errors in measuring the angle of the bearing.

 Another factor that reduces accuracy is the wide variation in the output of pyrotechnic thermal power sources.

 In accordance with the technical conditions, the time of their entering the mode is in all operating conditions ≤ 1.2 s.

In reality, they reach the mode after 0.3-0.4 s in normal climatic conditions and after 1.0-1.2 s at extreme operating temperatures (± 50 ^o C).

 The error of the clock mechanism of the T90 tube, with the help of which the initial time of engaging the on-board battery and sizing of the inertial gyroscope in accordance with its technical conditions is established, is ± 0.2 s.

 The above leads to a situation where the separation of the nasal block protecting the optical part of the homing head, unlocking of the homing head, after which it goes into active mode, and the appearance of a useful signal reflected from the target, spreads in time to a value when the homing head is quite long time can be affected by optical interference, which can lead to false capture and disruption of homing.

 The objective of this technical solution is to increase the accuracy of involving on-board systems of the projectile.

The problem is achieved in that in the known method, including setting the time for the on-board systems of the guided projectile to be activated, the entire range of firing ranges is divided into separate sections, each section is assigned a corresponding code, time intervals Δt ₁ -Δt _n are formed for each section to engage the on-board systems of the projectile which are sewn up in ROM, and before firing, a code is set corresponding to the selected section of the firing ranges, according to which during the flight the use of ROMs of time intervals wired into it for activating onboard systems of a guided artillery shell.

The proposed method can be implemented in the device shown in the drawing, where:
1 - magnetic pulse generator driven by barrel overload (inductor), consisting of a moving core inductance coil;
2 - on-board pyrotechnic thermal battery with electric igniter, for example T514A;
3 - a clock generator, made, for example, according to the scheme given in OST 11340107-80, p. 206, drawing 356;
4 - toggle switch, made, for example, on the switches 9E140 (PE3.183.002 TU);
5 - memory unit (ROM), made, for example, on 556 RT5 chips;
6 - circuit And, made, for example, on the chip 564LA7;
7 - counter, made, for example, on 564 IE10 chips;
8 - trigger, made, for example, on the chip 564 TM2;
9 - reset circuit to zero, performed, for example, according to the circuit shown in the book of P. Horowitz, W. Hill "The Art of Circuit Engineering", T1, p. 558, fig. 8.77.

 The device operates as follows.

 Choose the type of artillery system, for example, D-20, 2SZM, for which a guided artillery shell with a homing head has been developed.

Calculate the range of possible trajectories of firing a given projectile for these systems for all firing ranges provided for these systems. The entire range of ranges is divided into a number of sections, each of which is assigned a specific code. A table is compiled, in which the ranges of firing ranges of each section, the codes corresponding to each section, and the operating times of the on-board systems of the projectile: inertial gyroscope Δt ₁ , disclosure of the rudders Δt ₂ , engagement of batteries for the homing head Δt ₃ , separation of the nose block Δt ₄ and t .d.

The data of this table Δt ₁ -Δt _{n are} recorded in the memory unit 5 in the manufacture of electronic equipment of the projectile.

In addition, each code has its own range of firing ranges. For example, when shooting from 2 to 5 km, where the same time sequence will operate, the time intervals Δt ₁ -Δt _{n are} constant - one code.

For firing portion ranges from 5 to 7 km - other code other values Δt ₁ -Δt _n and so on, and at the first output of the storage unit 5 is formed by a time interval Δt _1, the second - Δt ₂ and so on depending on the number of systems required to engage in the flight process.

 Before shooting, when the coordinates of the target are determined, information about the firing range, type of fuse, direction and angle of throwing is received at the firing position.

 The charger sets on the tumbler register 4 switches located on the projectile in position, the code of which corresponds to a given range, and charges the gun. Let, for example, all the switches be turned off, which corresponds to the code 000 (if there are 3 such switches), and let this code correspond to the initial range of firing ranges, for example, from 2 to 5 km.

 When fired from overloads acting on the projectile, the inductor 1 is triggered, the electric current pulse of which is activated by the electric igniter of the on-board pyrotechnic heat battery 2 and drives it.

 The voltage of this battery is used to power the electronic equipment of the projectile.

 When the battery 2 enters the mode, the reset circuit to zero 9 generates a pulse, which from its output goes to the second input of the counter 7 and resets it, as well as to the first R-input of the trigger 8, and the "logical" signal appears on the inverse output of this trigger. 1 ", which enters the second input of the And 6 circuit, allowing the passage through it of clock pulses from the generator 3, arriving at its first input.

 From the output of circuit And 6, clock pulses are supplied to the first counting input of counter 7 and the countdown of time intervals begins.

From the outputs of counter 7, the signals are fed to the lower address inputs 2 of the memory block 5, to the senior address inputs 1 of which the code from the toggle register 4 is received. Under the action of these signals, the signals at the outputs of the memory block 5 sequentially appear at the moments corresponding to the time intervals Δt ₁ -Δt _n

 At the end of the last signal involving the last of the necessary elements of the projectile, this signal is simultaneously fed to the second S-input of trigger 8 and puts its inverse output to zero, thereby stopping the arrival of clock pulses to the counting input of counter 7.

Thus, by the expiration of the last time interval Δt _n , that is, by the time the projectile enters the homing zone, all projectile systems are prepared to work independently of each other, in any sequence with high accuracy, ensuring firing at any trajectories.

Sources of information
1. A 152-mm round of a ZVOF64 (ZVOF93) with a high-explosive fragmentation guided projectile ZOF39 and a charge of N 1 (reduced variable charge). Technical description and instruction manual ZVOF64.00.00.000 TO (ZVOF9Z.00.00.000 TO), M .: Military Publishing House, 1990, p. 56-64.

Claims (1)

 A method of firing an artillery guided projectile with a homing head, including setting the time for the onboard systems of the guided projectile to operate, characterized in that the entire range of firing ranges is divided into separate sections, each section is assigned a corresponding code, time intervals are formed for each section to engage the onboard systems of the shell, which sewn up in ROM, and before firing, set the code corresponding to the selected area of the firing ranges, in accordance with which Processes flight is read from the ROM sewn into it time intervals for activating the onboard systems guided artillery projectile.