RU2191984C2 - Procedure to arm airborne systems of guided projectile - Google Patents

Abstract

FIELD: armament , specifically, artillery guided projectiles with laser homing head. SUBSTANCE: clock mechanism is set in motion under action of barrel overload, after expire of time set in clock mechanism inertial gyroscope is uncaged, airborne storage battery feeding airborne equipment is armed and storage batteries of homing head are reset from it in sequence. When one storage battery of homing head achieves operational condition nose unit is shot off opening entrance pupil of homing head. Vanes of steering drive open by lock-on signal formed by homing head after it begins reception of signals reflected from target. EFFECT: raised precision of guidance. 1 dwg

Description

 The invention relates to the field of armament, in particular to artillery guided projectiles with a laser homing head.

 A known method of cocking on-board systems of a guided projectile [1], which consists in the fact that under the influence of barrel overload, the clock mechanism is started, after the time set in the clock mechanism, the gyroscope is inertial, the power supply of the on-board equipment is charged, the head power batteries are sequentially charged from it homing, from one of which they shoot the bow block, opening the entrance pupil of the homing head, open the steering wheels.

 The disadvantage of this method is that when using an air-dynamic steering drive operating on a free flow in the control system, in the absence of control commands, the latter is in zero-hold mode (self-oscillations relative to the zero position within units of degrees occur). This mode during the flight of the projectile leads to an increase in inductive resistance and to an increase in the drag coefficient Cx, which leads to a decrease in the projectile speed, an increase in technical dispersion and to a deterioration in the dynamics of the air-dynamic drive in the final guidance section, which reduces the accuracy of guidance.

 The objective of this proposal is to increase the accuracy of guidance of guided projectiles. The problem is achieved in that in the method of charging the onboard systems of the guided projectile, which consists in the fact that under the action of the barrel overload the clockwork is started, after the time set in the clockwork expires, the inertial gyroscope is uncovered and the battery of the onboard equipment is charged, the battery is sequentially charged from it homing power batteries, when entering the mode of one of the homing power batteries, the nasal block is fired, opening the entrance pupil of the homing head Disclose steering drive wheels, the disclosure of rudders steering drive is performed by the signal "seizure" formed homing after the beginning of reception signals reflected from targets.

 The exception in the known method of operating time of the air-dynamic drive in the zero-hold mode from the moment the rudders open until the control commands from the homing head are received on them eliminates the influence of the drive operation on technical dispersion (projectile speed) and thereby improves the accuracy of guidance.

 The proposed method of cocking the onboard systems of a guided projectile can be implemented, for example, in the device shown in the drawing, where 1 is the homing head, 2 is the clock mechanism, 3 is the bow block, 4 is the inertial gyro with a lamella sensor, 5 is the steering gear, 6 - power supply, 7 - circuit I, 8 - circuit OR, 9, 10, 11, 12, 13 - first, second, third, fourth and fifth power amplifiers, 14, 15, 16, 17 - first, second, third and fourth steering control windings, 18, 19, 20 - homing power batteries, 21 - on-board power battery ry, while the elements 1-21 are made, for example, as in the prototype.

 The device operates as follows.

 When fired from a striking gun through a capsule sleeve, a propellant is ignited and under the influence of gas pressure the projectile is fired from the gun.

 Under the influence of barrel overload, the clockwork starts 2. After the time previously set in the clockwork, it generates a pulse, which from its output goes to the electric igniters of the inertial 4 gyroscope and the onboard equipment battery 21, while the inertial gyroscope 4 is opened and the battery is turned on on-board equipment 21. When the rated voltage is reached under the influence of the latter, electric igniters of the batteries of the homing head 20 (used for Itani its electronic apparatus), 18 (which serves for the power correction windings) and 19 (serving to a photoreception device). These batteries enter the mode and under the influence of the voltage on the battery 18, an electric igniter of the nose unit 3 is cocked and the latter is fired off, opening the entrance pupil of the homing head for receiving input signals reflected from the target.

 When approaching the capture zone, the head receives signals reflected from the target, and after analyzing them, it generates a "Capture" signal and control commands on the channels "+ Y" "-Y", "+ Z", "-Z".

 Under the action of the signal "Capture", incoming through the first power amplifier 9 to the electric igniter of the steering wheel opening mechanism 5, the latter are opened.

 At the same time, the “Capture” signal is fed to the first input of the And 7 circuit, allowing the passage of the gravity compensation signal from the output of the 2 lamella sensor through its second input to the Compensation input of the homing head and to the second input of the OR 8 circuit, to the first input of which the signal " -Y "from the output of the homing head. From the output of the circuit OR 8 signal "-U goes to the second power amplifier 10.

 The inputs of the third, fourth and fifth power amplifiers respectively receive signals "+ Y", "+ Z" and "-Z".

 From the outputs of power amplifiers 10-13, control signals are supplied to the first inputs of the corresponding control windings 14-17, the second inputs of which are connected to the power source of the onboard control equipment 21.

 Under the influence of these signals, the rudders deviate and thereby direct the projectile at the target.

 In this case, runtime of the steering gear in zero-hold mode from the moment the rudders open until the “Capture” signal arrives is eliminated, which made it possible to exclude the influence of the rudders on the flight of the projectile in an uncontrolled section and thereby increase the accuracy of its guidance.

Sourse of information
"152-mm round ZVOF64 (ZVOF93) with a high-explosive fragmentation-guided projectile ZOF39 and charge 1 (Reduced variable charge). Technical description and instruction manual for ZVOF64.00.00.000TO (ZVOF93.00.00.000TO)." Moscow. Military publishing house. 1990, pp. 56-64.

Claims (1)

 The method of charging the onboard systems of a guided projectile, namely, that under the action of the barrel overload, the clockwork is started, after the time set in the clockwork expires, the inertial gyroscope is uncovered and the power supply of the onboard equipment is charged, the batteries of the homing head are sequentially charged from it on the mode of one of the batteries of power for the homing head they shoot the nasal block, opening the entrance pupil of the homing head, open the steering wheels, I distinguish iysya in that the steering drive wheels on the open signal "seizure" formed homing after the start of its signals reflected from targets.