RU2398182C1 - Method to control rocket high-explosive warhead killability field characteristics and device to this end - Google Patents

Abstract

FIELD: weapons and ammunition. ^ SUBSTANCE: proposed method consists in using two target contactless pickups operating in different ranges of electromagnetic spectrum, locking the target and defining target flight side at notable misses by target radiometric pickup, locking the target and defining target flight side at insignificant misses by target optical pickup. Firing instruction is generated by electronic unit of delay time computation. Killability field towards the target is generated by sending "go" instruction to actuator with its terminal assembly shifted towards side opposite target flight side. Additionally, target location sector with respect to rocket lengthwise axis is determined proceeding from comparison of polarity of signals from azimuth and elevation angle pickups. Target selection is performed by spatial attribute proceeding from comparison of target flight side determined by radiometric and optical pickups of target. Proposed device comprises contact target pickup, radiometric contactless pickup, optical contactless pickup, firing delay time computation unit incorporating device that generates instruction for actuator with its terminal assembly shifted towards side opposite target flight side. ^ EFFECT: higher noise immunity. ^ 3 cl, 4 dwg

Description

The invention relates to defense technology and can be used to create warheads, in particular for high-precision guided missiles or missiles of small and medium caliber.

Closest to the invention is a method for controlling the characteristics of the field of destruction of a high-explosive fragmentation warhead of a rocket, which consists in emitting two non-contact target sensors operating in different ranges of the electromagnetic spectrum, in fixing the target and determining the side of its span in large misses by the radiometric target sensor, in fixing the target and determining the side of its span for small misses with an optical target sensor, forming a team to detonate the electronic unit for calculating the delay time, forming a field reflections in the direction to the target by issuing a command to actuate the safety-executive mechanism, the end node of which is shifted to the side opposite to the side of the span of the target [1].

Closest to the invention is a device for controlling the characteristics of the field of destruction of a high-explosive fragmentation warhead of the rocket, which contains a contact target sensor, a radiometric non-contact target sensor for fixing the target and determining the side of the span for large misses, an optical non-contact target sensor for determining the side of the span for small misses, as well as an electronic unit for calculating the delay time of the blasting, equipped with a device that provides a command to operate the fuse o-actuator, the end node of which is offset to the side opposite the side of the target’s flight, a high-explosive fragmentation warhead of directional circular action, characterized by the presence of a bursting charge and an explosive device including safety-actuating mechanisms, the end nodes of which are radially offset relative to the axis of the charge [ one].

The disadvantages of the data of the method and device is the low noise immunity due to the non-use of preliminary information on the spatial position of the target, obtained on the basis of the analysis of the polarity of the signals from the azimuth sensors and elevation angle of the homing head.

An object of the invention is to increase noise immunity due to spatial target selection.

The solution to the technical problem is achieved by the fact that in the method of controlling the characteristics of the field of destruction of a high-explosive fragmentation warhead of the rocket, including the radiation of two non-contact target sensors operating in different ranges of the electromagnetic spectrum, fixing the target and determining the side of its span on large misses by the radiometric target sensor, fixing the target and determination of the side of its flight on small misses with an optical target sensor, the formation of a team to detonate the delay time calculation by the electronic unit, the formation of the floor defeat in the direction of the target by issuing a command to actuate the safety-actuating mechanism, the end node of which is shifted to the opposite side of the span of the target, an additional command to actuate the safety-actuating mechanism is formed taking into account a predetermined sector of finding the target relative to the longitudinal axis of the rocket based on comparing the polarity of signals from azimuth and elevation sensors and target selection based on spatial characteristics based on a comparison of the sector REPRESENTATIONS goals and hand-flight goals defined radiometric and optical sensors goal.

The inventive method is implemented in a device for controlling the characteristics of the field of destruction of a high-explosive fragmentation warhead of a rocket, directionally circular in action with a bursting charge and an explosive device including safety-actuating mechanisms, the end nodes of which are radially offset relative to the charge axis containing the target’s contact sensor, radiometric non-contact sensor targets for fixing the target and determining the side of the span for large misses, an optical non-contact target sensor designed to detect the side of the span on small misses, as well as an electronic unit for calculating the time of the delay of detonation with a device that provides a command for the operation of the safety-executive mechanism, the end node of which is shifted to the side opposite to the side of the span of the target, characterized in that it is additionally equipped with azimuth and angle sensors tilt installed in the homing missile, target selection unit, the first, second, third and fourth inputs of which are connected respectively to the inputs of the receiving antennas of the radio a metric non-contact target sensor, inputs of receiving antennas of an optical non-contact target sensor, an azimuth sensor and a tilt angle of the homing head, and the first and second outputs of the target selection unit are connected to the first and second inputs of the electronic unit.

In addition, the target selection unit is made of the first, second, third and fourth diodes, the first, second, third and fourth elements AND, the first, second, third, fourth, fifth, sixth, seventh and eighth keys, the first and second elements OR, the first, second, third and fourth inputs of the target selection unit are connected to the first inputs of the fifth, sixth, seventh, eighth, first, second, third, fourth keys, with the inputs of the first and simultaneously second diodes, with the inputs of the third and simultaneously fourth diodes, first the second and third diodes are connected according to the reverse connection circuit, the second and fourth are connected according to the direct connection circuit, the outputs of the first, second, third and fourth diodes are connected respectively to the first inputs of the second and third, first and fourth, the second input of the third, the second inputs of the fourth, second and the first elements And, the outputs of the first, second, third and fourth elements And are connected to the second inputs of the first and fifth, second and sixth, third and seventh, fourth and eighth keys, the outputs of the first, of the second, third and fourth keys are connected to the inputs of the first OR element, the outputs of the fifth, sixth, seventh and eighth keys are connected to the inputs of the second OR element, the outputs of the second and first OR elements are the first and second outputs of the target selection block, respectively.

New features that have significant differences in the method is the following set of actions.

1. The command to actuate the safety-executive mechanism is formed taking into account a predefined sector of finding the target relative to the longitudinal axis of the rocket.

2. The sector of finding the target relative to the longitudinal axis of the rocket is determined by comparing the polarity of the signals from the azimuth sensors and the elevation angle of the homing missile.

3. The target selection by spatial feature is determined based on a comparison of the target location sector and the target span, determined by radiometric and optical target sensors.

New elements with significant differences in the device are: azimuth and inclination sensors installed in the homing missile, target selection unit.

Figure 1 shows a structural diagram of a device for controlling the characteristics of a field of destruction of a high-explosive fragmentation warhead of a rocket; Figure 2 is a structural diagram of a device for controlling characteristics of a field of destruction of a fragmentation of a high explosive fragmentation warhead of a rocket; 3 is a diagram for determining a sector of finding a target relative to the longitudinal axis of a rocket; FIG. 4 is a structural diagram of a block for selecting a target.

A device for controlling the characteristics of the field of destruction of a high-explosive fragmentation warhead of a rocket (Fig. 1) contains an explosive charge 1 and an explosive device including safety-actuating mechanisms 2a and 2b, a contact target sensor 3, a radiometric non-contact target sensor containing a radiating 4 and receiving 5 antenna , designed to fix the target and determine the side of the span for large misses, unit for calculating the delay time of the undermining 6.

An explosive device is equipped with a multi-channel optical non-contact target sensor containing emitting channels 7a and 7b and receiving channels 8a and 8b, designed to determine the side of the span 9 in small misses, while the electronic unit for calculating the delay time of the blasting 6 is equipped with a device 10 that provides a safety signal for operation -executive mechanism 2a or 2b, the end node of which is radially offset relative to the axis of the charge in the direction opposite to the side of the span.

Block 11 target selection consists of the first 12, second 13, third 14 and fourth 15 diodes, the first 16, second 17, third 18 and fourth 19 elements And, the first 20, second 21, third 22, fourth 23, fifth 24, sixth 25 , seventh 26 and eighth 27 keys, the first 28 and second 29 elements OR, the first, second groups, the third and fourth inputs of the selection block 11 are connected to the first inputs of the fifth 24, sixth 25, seventh 26, eighth 27, first 20, second 21, third 22, fourth 23 keys, simultaneously with the inputs of the first 12 and second 13 diodes, simultaneously with the input the third 14 and fourth 15 diodes, the first 12 and third 14 diodes are connected according to the reverse connection circuit, the second 13 and fourth 15 diodes are connected according to the direct connection circuit, the outputs of the first 12, second 13, third 14 and fourth 15 diodes are connected respectively to the first inputs second 17 and third 18, first 16 and fourth 18, second input of the third 18, second inputs of the fourth 19, second 17 and first 16 elements AND, outputs of the first 16, second 17, third 18 and fourth 19 elements And connected to the second inputs, respectively, of the first 20 and fifth 24, t horn 21 and sixth 25, third 22 and seventh 26, fourth 23 and eighth 27 keys, the outputs of the first 20, second 21, third 22 and fourth 23 keys are connected to the inputs of the first 28 element OR, the outputs of the fifth 24, sixth 25, seventh 26 and the eighth of 27 keys is connected to the inputs of the second 29 OR elements, the outputs of the second 29 and the first 28 OR elements are the first and second outputs of the target selection block 11, respectively.

The proposed device operates as follows.

The radiometric non-contact target sensor, which is part of the explosive device, detects the target and, in case of a miss, the magnitude of which exceeds the distance between the emitting 4 and receiving 5 antennas, determines the side of the span with discreteness along the equatorial angle, determined by the number of pairs of emitting and receiving antennas. An optical non-contact target sensor probes the surrounding space to a depth determined by its sensitivity. In the case of a miss, the value of which is less than the limit for the optical NDC, the optical signal sent by its emitting channel 7b, reflected from the surface of the target 9 and received by the receiving channel 8b, is perceived by the receiving unit of the optical NDC. This also provides the determination of the side of the span with discreteness on the equatorial angle, determined by the number of pairs of emitting and receiving blocks (figure 1).

Implementation of spatial target selection is as follows.

The signals from the outputs of the receiving antennas (5, 8a) of the radiometric and optical sensors are fed to the first and second group of the target selection unit 11, to the third and fourth input of which signals from the azimuth and elevation sensors are received.

In case of coincidence in the spatial position of the target, determined on the one hand by one of the outputs of the receiving antennas (5, 8a) of the radiometric and optical sensors, and on the other hand by the target selection unit, the signals are sequentially transmitted to the first and second inputs of the electronic unit 6 for calculating the delay time undermining (figure 2).

The signals from the sensors of the azimuth and elevation angle of the homing missile head are fed to the third and fourth inputs of the target selection unit 11 and, respectively, to the inputs of the first 12 and simultaneously the second 13 diodes, the third 18 and simultaneously the fourth 19 diodes, the outputs of which, depending on the polarity of the signals, are fed to the first inputs of the second 17 and third 18 elements And, respectively, the first 16 and fourth 18 elements, the second inputs of the third 18 elements And, the second inputs of the fourth 19, second 17 and the first 16 elements I.

Depending on the target location sector (Fig. 3), the signal from the output of one of the And elements (first 16, second 17, third 18 and fourth 19) is supplied to the second inputs of the first 20 and fifth 24, or the second 21 and sixth 25, respectively third 22 and seventh 26, or fourth 23 and eighth 27 keys, to the first inputs of one of the keys (fifth 24, sixth 25, seventh 26 and eighth 27), depending on the side of the span of the target, the signal comes from one of the outputs of the receiving antenna 5 radiometric sensor, at the first inputs of one of the keys (first 20, second 21, third 22 th, fourth, 23), depending on the objective side of the span, the signal is supplied from one of the receiving antennas 8a optical sensor target (4).

In case of coincidence of the sector and the direction of the side of flight of the target, determined by the radiometric sensor, the signal from the output of one of the keys (fifth 24, sixth 25, seventh 26 and eighth 27) is fed to one of the inputs of the second 29 OR elements.

In the case of coincidence of the sector and the direction of the side of flight of the target, determined by the optical sensor, the signal from the output of one of the keys (first 20, second 21, third 22 and fourth 23) is fed to one of the inputs of the first 28 OR elements.

The signals from the outputs of the second 29 and the first 28 elements And are sequentially fed to the first and second inputs of the electronic unit 6.

Upon receipt of a signal about the appearance of the target and the side of its span, the electronic unit 6 calculates the delay time of the blasting by the values of the relative speed and the angle of meeting, after implementation, the device 10 issues a command to actuate the safety-actuating mechanism 2b radially offset from the charge axis to the side opposite to the side span corresponding to the equatorial direction of the transmitting and receiving channels 7b and 8b of the optical multi-channel sensor.

Thus, the use of the proposed device will increase the noise immunity due to the spatial selection of the target.

Information sources

1. RF patent for the invention No. 2301958, class. F42B 15/00, dated June 27, 2007

Claims (3)

1. A method for controlling the characteristics of the field of destruction of a high-explosive fragmentation warhead of a rocket, including the radiation of two non-contact target sensors operating in different ranges of the electromagnetic spectrum of the target, fixing the target and determining the side of its span on large misses with a radiometric target sensor, fixing the target and determining the side of its span on small misses with an optical target sensor, the formation of a team to undermine the electronic unit for calculating the delay time, the formation of the lesion field in the direction of the target by feeding to a command for operating the safety-executive mechanism, the end node of which is shifted to the opposite side of the target span, characterized in that the command for operating the safety-executive mechanism is formed taking into account a predetermined sector of finding the target relative to the longitudinal axis of the rocket based on a comparison of the polarity of the signals from the sensors azimuth and elevation angle and target selection by spatial attribute based on a comparison of the target location sector and the target span, determine with radiometric and optical target sensors. 2. A control device for the characteristics of the field of destruction of a high-explosive fragmentation warhead of a directional circular missile with a bursting charge and an explosive device including safety-actuating mechanisms, the end nodes of which are radially offset from the axis of the charge, containing a contact target sensor, a radiometric non-contact target sensor for fixing goals and determining the side of the span for large misses, an optical non-contact sensor of the target for determining the side of the span for small misses, and an electronic unit for calculating the delay time of detonation with a device that provides a command for the operation of the safety-actuating mechanism, the end node of which is shifted to the side opposite to the span of the target, characterized in that it is equipped with azimuth and inclination sensors installed in the homing missile, unit target selection, the first, second, third and fourth inputs of which are connected respectively to the inputs of the receiving antennas of the radiometric non-contact target sensor, the inputs of the receiving ntenn optical non-contact sensor target, the sensor and the azimuth angle of the homing head and the first and second outputs of the selection block are connected to first and second inputs of the electronic unit. 3. The device according to claim 2, characterized in that the target selection unit is made of the first, second, third and fourth diodes, the first, second, third and fourth elements AND, the first, second, third, fourth, fifth, sixth, seventh and the eighth keys, the first and second elements OR, while the first, second, third and fourth inputs of the target selection unit are connected to the first inputs of the fifth, sixth, seventh, eighth, first, second, third, fourth keys, with the inputs of the first simultaneously and second diodes , with third and simultaneous inputs of the fourth diodes, the first and third diodes are connected according to the reverse connection circuit, and the second and fourth diodes are connected according to the direct connection circuit, the outputs of the first, second, third and fourth diodes are connected respectively to the first inputs of the second and third, first and fourth, second inputs of the third , the second inputs of the fourth, second and first elements And, the outputs of the first, second, third and fourth elements And are connected to the second inputs of the first and fifth, second and sixth, third and seventh, fourth o and the eighth key, the outputs of the first, second, third and fourth keys are connected to the inputs of the first OR element, the outputs of the fifth, sixth, seventh and eighth keys are connected to the inputs of the second OR element, the outputs of the second and first OR elements are the first and second outputs of the block target selection.

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