RU2251069C1 - Tandem type warhead - Google Patents

Tandem type warhead Download PDF

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Publication number
RU2251069C1
RU2251069C1 RU2003130382/02A RU2003130382A RU2251069C1 RU 2251069 C1 RU2251069 C1 RU 2251069C1 RU 2003130382/02 A RU2003130382/02 A RU 2003130382/02A RU 2003130382 A RU2003130382 A RU 2003130382A RU 2251069 C1 RU2251069 C1 RU 2251069C1
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RU
Russia
Prior art keywords
warhead
target
charge
leading
explosive
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RU2003130382/02A
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Russian (ru)
Inventor
н В.А. Авен (RU)
В.А. Авенян
А.Е. Курепин (RU)
А.Е. Курепин
В.В. Гришин (RU)
В.В. Гришин
Б.А. Говоруха (RU)
Б.А. Говоруха
А.М. Малинин (RU)
А.М. Малинин
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ФГУП "ГосНИИМаш"
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Priority to RU2003130382/02A priority Critical patent/RU2251069C1/en
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Publication of RU2251069C1 publication Critical patent/RU2251069C1/en

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Abstract

FIELD: military equipment, may be used for building of guided rockets' high accuracy warheads of small and middle diameter, designed for destroying lightly armored and unarmored techniques, and also enemy's infantry in localities and in the shelters.
SUBSTANCE: tandem type warhead has a primary charge, a leading high-explosive charge placed in the cavity of the fairing, a steering compartment placed between primary and leading charges and blasting arrangement with target's sensors , safety and executive mechanism, electronic retainer block and electric circuits. The leading and primary charges' bodies have prepared damaging elements, blasting arrangement which is provided with non-contact target's sensors evenly located along circumference of lateral surface of its body with directional diagram oriented perpendicularly to the warhead's axle and contacted sensors of the target with directional diagram oriented along the warhead's axle. Electronic retainer block is included into the electric circuit connecting contacted target's sensor and safety and executive mechanism of the primary charge.
EFFECT: increases warhead's high-explosive effects.
1 cl, 3 dwg

Description

The invention relates to defense equipment and can be used to create warheads of high-precision guided missiles of small and medium caliber, designed to destroy lightly armored and unarmored vehicles, as well as located on the ground and in shelters of enemy personnel.

Known high-explosive fragmentation warheads (OFBCH) guided missiles and shells of the class "ground-to-ground" or "air-to-ground", for example, according to the patent of the Russian Federation No. 2018779, MKI 5 F 42 V 12/32, publ. 08/30/94, bull.

OFBCH according to the specified patent contains a bursting charge with a fragmentation shell and fuse, which includes a contact target sensor and a safety-actuating mechanism, interconnected by an electric circuit. This warhead defeats targets through a joint high-explosive fragmentation and is designed to combat such targets of the battlefield as lightly armored or unarmored vehicles, aircraft and helicopters in parking lots, manpower in open areas and in artificial or natural shelters.

Contact-action fuses used in these OFBCHs usually have two operation modes - “instant” or “slow”. In this case, the fuse is set to “instant” or “slow” operation by switching the fuse circuits before launching the rocket (projectile) at the operator’s command. Installation on the “instantaneous” action is made to ensure that warheads are triggered on the target’s surface when firing at lightly armored or unarmored vehicles, aircraft and helicopters in parkings, and manpower located in open areas. When shooting at manpower located in natural or artificial shelters, such as long-term protective defensive structures (DZOS), trenches or trenches, when to increase the effectiveness of the action it is necessary to increase the amount of destruction of the protective thickness of the shelter, the bursting charge must be buried in the ground, protecting the shelter from high-explosive fragmentation warhead. For this, the fuse is set to "slow" action.

To minimize the fuse’s response time in the “instant” mode, contact target sensors are usually placed in the head of the front compartment of the rocket (projectile). This allows you to provide the fastest possible information about the approach of the missile to the target. However, even in this case, the response time of the explosive device from the moment the head part of the rocket (projectile) touches the target surface to undermine the bursting charge is several hundred microseconds, which includes the time required for the contact sensor to fire and the time for the operation of the safety-actuator assemblies. When working on soft soils at a speed of approaching the target of the rocket (projectile) of the order of several hundred meters per second, during the “instant” fuse operation, the rocket travels a distance of the order of its caliber. This leads to the operation of a bursting charge, already partially buried in the ground. Soil shields a significant part of the flying fragmentation shell of a bursting charge, reducing the effectiveness of fragmentation on targets located on the surface and preventing the defeat of targets hidden in the folds of the terrain. In addition, the placement of the target’s contact sensor in the front of the rocket’s front compartment leads to additional screening of the front hemisphere by the sensor and its mounting structural elements in the compartment and to reduce fragmentation in this direction.

When operating in the “instant” response mode on targets with a solid body, such as lightly armored vehicles, placing a contact sensor in the head of the front rocket compartment causes a burst charge to be triggered away from the target’s surface, thereby preventing the maximum possible burst charge approximation to the surface of the target and reducing the value of the joint high-explosive fragmentation.

In addition, contact action target sensors have limitations on response conditions at small angles of approach to the target surface. So, for example, the 9E277 explosive device is known (see, for example, the technical description and operating instructions СЩI.300.042 ТО), which contains a safety-actuating mechanism and a contact target sensor - a piezoelectric type product 9E273 ПГ. The design and operation principle of this target sensor does not allow it to provide reliable operation at angles of approach to the target surface of less than 15 °.

The well-known reaction-type target sensors placed in the missile’s head, built on the principle of closing two conductive surfaces at the moment of deformation of the fairing, also do not provide reliable operation at small angles of approach to the target’s surface, especially if the angle of approach is less than the taper angle of the fairing of the warhead. In this case, for example, when approaching soft soil, the rocket body will slide along its surface without deformation of the fairing until the rocket is buried into the ground by at least half a caliber. This leads to the fact that the operation of the bursting charge occurs in a buried position of at least half the diameter in the ground. Soil shields a significant part of the expanding fragmentation shell of the explosive charge, reducing the effectiveness of fragmentation on targets located on the soil surface and preventing the defeat of targets hidden in the folds of the terrain.

The inclusion of additional non-contact target sensors in the blasting device on the electromagnetic principle does not provide the required accuracy, since known sensors based on the use of radio emission or magnetometric methods of fixing the target have a large spread in response range, which, with flat missile trajectories, leads to large errors in response to span, reaching at angles of approach to the surface of the earth of the order of 3-5 degrees of values of the order of hundreds of meters.

So, for example, the known design of the warhead of the tandem type, intended for use in anti-tank and anti-aircraft guided missiles (for example, according to the patent of the Russian Federation No. 2046281, MKI 6 F 42 V 12/10, publ. 20.10.95 bul. No. 29), containing the main and leading charges, an explosive device including a reaction-type contact target sensor (in the form of two isolated contacts) and non-contact target sensors on the electromagnetic principle, safety-actuating mechanisms, an electronic delay unit and electrical circuits. The warhead of the tandem type described in this patent is equipped with a leading charge of cumulative action and the main charge of multi-purpose, cumulative and high-explosive fragmentation.

The technical solution described in the said patent, as the closest to the claimed one according to the technical nature and the achieved technical result, was chosen as a prototype.

Signs of the prototype, common with the claimed design of high-explosive fragmentation warhead tandem type:

- main and leading charges,

- an explosive device with target sensors of contact and non-contact action, safety-actuating mechanisms, an electronic delay unit and electrical circuits,

- the steering compartment, located between the leading and main charges.

The specified prototype has disadvantages leading to a decrease in the effectiveness of high-explosive fragmentation.

A significant drawback of the design of the prototype is the use of the leading charge of the cumulative effect and the placement of the contact sensor of the target fuse in the head of the fairing.

The use of the leading charge of the cumulative effect significantly limits the meridional angle of expansion of the striking elements (fragments of the cumulative stream) formed when the leading charge is triggered. The main stream of fragments in this case only moves along the axis of the leading charge, which corresponds to a value of the meridional angle of expansion of approximately ± 2-3 °. The presence between the leading and main charges of the steering compartment leads to the fact that most of the fragmentation stream directed forward along the rocket flight formed by the main charge is shielded by the structural elements of the steering compartment.

Placing the contact sensor of the fuse target in the head part of the fairing leads to an additional screening of the fragment fragmentation field by the structural elements of the sensor and its attachment to the fairing.

Another significant disadvantage of the prototype is the use of a non-contact sensor on the electromagnetic principle. When launching a projectile from a ground-based launcher or low-flying helicopter at a target located at a distance of 3-5 kilometers, the angles of approach to the surface of the earth will almost always be within a few degrees. As noted above, well-known sensors based on the use of radio emission or magnetometric methods of fixing a target have a wide variation in the range of operation. With the fixed trajectories of the rocket, this leads to large errors of operation along the span, reaching at angles of approach to the surface of the earth of the order of 3-5 degrees values of the order of hundreds of meters, which leads to large misses and reduces the effectiveness of the action on targets located on the specified surface.

The problem to which the invention is directed, is:

- ensuring effective high-explosive fragmentation of the OFBCH as part of a guided projectile for targets located on the surface of the earth, when the projectile approaches this surface at small angles,

- increasing the efficiency of the joint high-explosive fragmentation of targets with a solid surface when the projectile approaches this surface at large angles.

Unlike the well-known warhead of the tandem type, containing the leading charge of the cumulative action and the main charge of the cumulative and high-explosive fragmentation action, an explosive device that includes a contact target sensor of the reaction type (in the form of two isolated contacts) and non-contact target sensors on the electromagnetic principle, actuators, electronic delay unit and electrical circuits, in the proposed warhead, a high-explosive fragmentation charge placed in the cavity of the fairing is used of the action, between the leading and the main charge the steering compartment is located, while the leading and main charge bodies contain ready-made striking elements, the fuse is equipped with non-contact optical target sensors arranged uniformly around the side surface of the body, whose radiation pattern is oriented perpendicular to the axis of the warhead, and contact sensors of the inertial action target, the radiation pattern of which is oriented along the axis of the warhead, and the electric unit hydrochloric delay is part of the electrical circuit connecting the contact sensor and the target-safety actuator main charge.

The leading high-explosive fragmentation charge is placed in a hemispherical body, oriented by the top of the hemisphere in the direction of the top of the fairing along the axis of the warhead, while in the case there are ready-made striking elements of spherical shape.

Technical solutions containing features that distinguish the claimed solution from the prototype are unknown and do not follow explicitly from the prior art. This suggests that the claimed solution is new and has a sufficient inventive step.

Each of the above essential features is necessary, and their combination is sufficient to achieve the novelty of the quality of the new super-effect, which is not inherent in the signs of their disunity.

The essence of the proposed technical solution is illustrated by graphic images in figure 1-3. Figure 1 shows a General view of the proposed high-explosive fragmentation warhead in section. Figure 2 illustrates the operation of the explosive charge of the warhead when the projectile approaches the surface of the earth at small angles (for example, about 5 °). Figure 3 illustrates the process of operation of the explosive charge of the warhead when approaching a solid surface of the target at an angle close to normal.

The proposed warhead for a guided projectile contains (Fig. 1) a cowl (1), an explosive device with active non-contact (2) and contact (3) target sensors, a leading high-explosive fragmentation charge (4), and a safety-actuating mechanism (5 ), the main high-explosive fragmentation charge (6) with a safety-executive mechanism (7). Positions (8) and (9), (10) and (11) show the front (along the flight) and rear boundaries of the meridional expansion angle of the fragmentation field of destruction, which is formed respectively by the leading and main charges. Position (12) indicates the steering compartment. Contact and non-contact target sensors, as well as an electronic delay unit, are installed in the fuse compartment located on the bottom of the main charge.

In figures 2 and 3, the position (13) conditionally shows the tail compartments of the rocket at the time of its approach to the target surface (14). In figure 2, the position 15 marks the value of the limiting range (N CR ) operation of non-contact sensors of the target.

The proposed warhead operates in two modes: non-contact and contact. In non-contact mode (figure 2) the operation of the warhead is as follows. After the distance between the non-contact target sensor (2) and the obstacle surface (14) becomes less than the maximum operating range (N CR ), the signal of the active non-contact sensor reflected from the target surface provides signals for the simultaneous operation of the safety-actuating mechanisms (5) and ( 7). This mode of operation provides a pre-contact detonation of the bursting charge, in which the conditions for deepening the bursting charge into the ground and screening of the fragmentation field of the ground damage are completely absent. At the same time, by choosing the limit of the response range of non-contact target sensors, it is possible to significantly increase the effectiveness of fragmentation effects, ensuring the defeat of elementary targets that shield each other on the ground or hidden in trenches or folds of the terrain.

In contact mode (figure 3) the work of the warhead is as follows. Upon impact with a solid target surface at angles close to normal, the warhead fairing (1) is deformed without noticeable force impact on the target’s contact sensors installed in the compartment of the fuse placed on the bottom of the main charge (6). The magnitude of the load on the contact sensors of the target will increase sharply only when approaching the solid surface of the target of the lead charge housing, which ensures the contact sensors are triggered and a signal is generated to undermine the PIM (5) leading charge (4). Undermining the leading charge in this case occurs at the moment of direct contact between its body and a solid barrier, which leads to an increase in the efficiency of the joint high-explosive fragmentation of the leading charge on a solid barrier.

The signal to detonate the main charge from the contact sensors is transmitted to the PIM (7) of the main charge (6) through the electronic delay unit, which ensures that the main charge is brought closer to a fixed distance to a solid barrier.

Undermining the main charge at a predetermined distance from the surface of a solid obstacle that previously suffered damage at the moment the leading charge was triggered, increases the efficiency of the high-explosive fragmentation warhead on the considered obstacle. At the same time, by choosing the delay time of the response of the main charge, it is possible to significantly increase the efficiency of the fragmentation effect on the internal or external structural elements of the target, realizing either a buried mode or precontact operation for the main charge.

The use in the composition of warheads of a leading high-explosive fragmentation charge, the meridional angle of expansion of the fragmentation damage field in which lies within 0-φ L Max , provides the elimination of screening by the steering compartment of the front (along the flight) part of the fragmentation lesion field formed by the main charge, which increases the effectiveness of the warhead on the target in the direction of which the rocket was launched.

The rear (in flight) boundary of the angle of expansion of the fragmentation field of destruction, determined by the value of φ ABOUT Max , is set based on the actual conditions of use of the rocket, which is equipped with the proposed warhead. Such conditions limiting the maximum value of the meridional angle of expansion may include requirements for ensuring the safety of the carrier in the conditions of warhead operation at a small distance from the launch site immediately at the time of commissioning of the PIM. In addition, fragments with values of the meridional angle of expansion close to 180 ° move almost in the opposite direction to the rocket movement, and therefore make a small contribution to the damaging effect of warheads.

The boundary value of the meridional angle of the main part of the fragmentation flow is determined by the direction of the normal to the surface of the fragmentation shell in its end zone. A small number of fragments (up to 5% of their total number), flying at angles greater than the boundary value, in the proposed warhead are shielded by the fuse and tail sections of the rocket. Therefore, when constructing the profile of the rear (in flight) part of the fragmentation shell, it is advisable to place the radius of curvature of the end zone of the fragmentation shell on the extension of the straight line passing through the front (in flight) edge of the explosive device and the end of the fragmentation shell (see Fig. 1).

The proposed technical solution was implemented in the development of high-explosive fragmentation warhead (OFBCH) for guided missiles of medium caliber. The developed OFBCH is located in two rocket compartments. The leading charge compartment contains a fairing, a leading high-explosive fragmentation charge placed in a hemispherical body containing ready-made striking elements of spherical shape, oriented by the top of the hemisphere in the direction of the fairing tip along the warhead axis, and PIM. The main charge compartment contains the main high-explosive fragmentation charge placed in a housing containing ready-made spherical-shaped striking elements, a PIM and a non-contact contact target sensor (NDC), which includes an electronic PIM primary delay unit that operates when the contact operation mode is implemented .

NKDC contains four active non-contact target sensors of optical action, placed evenly around the circumference of its own housing, which is part of the main charge compartment. The directional diagram of these sensors is oriented perpendicular to the warhead axis, and the maximum response range depends on the whiteness coefficient of the reflecting surface and is equal to 2-3 caliber rockets. In addition, the NCC contains contact target sensors whose radiation pattern is oriented along the warhead axis. Sensors are installed inside the NKDC housing on its end surface. The issuance of a command to operate from this sensor occurs when the specified value of the braking overload, which is valid for a specified period of time, is reached.

Evaluation of the effectiveness of the damaging effect of a rocket equipped with a tandem-type warhead developed in accordance with the proposed technical solution shows the high efficiency of the high-explosive fragmentation warheads for targets such as lightly armored and unarmored vehicles, manpower on the ground, in cars and buildings.

Claims (2)

1. High-explosive fragmentation warhead of the tandem type, containing the main charge, the leading charge located in the cavity of the fairing, the steering compartment, located between the main and leading charges, and an explosive device with target sensors, safety-actuating mechanisms, an electronic delay unit and electrical circuits , characterized in that the leading charge is made of high-explosive fragmentation, the buildings of the leading and main charges contain ready-made striking elements, and the explosive device is equipped with evenly around the circumference of the side surface of its body with non-contact target sensors, the radiation pattern of which is oriented perpendicular to the axis of the warhead, and contact target sensors, the radiation pattern of which is oriented along the axis of the warhead, and the electronic delay unit is part of the electrical circuit connecting the contact sensor of the target and safety - Executive mechanism of the main charge.
2. The warhead according to claim 1, characterized in that the leading charge body is made hemispherical, oriented by the top of the hemisphere in the direction of the top of the fairing along the axis of the warhead, and contains ready-made damaging elements of spherical shape.
RU2003130382/02A 2003-10-14 2003-10-14 Tandem type warhead RU2251069C1 (en)

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Cited By (16)

* Cited by examiner, † Cited by third party
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RU2456535C1 (en) * 2011-02-15 2012-07-20 Николай Евгеньевич Староверов Staroverov hollow-charge shell (versions)
RU2479825C1 (en) * 2011-11-07 2013-04-20 Федеральное государственное унитарное предприятие "Российский Федеральный ядерный центр - Всероссийский научно-исследовательский институт экспериментальной физики" - ФГУП "РФЯЦ-ВНИИЭФ" Precision shell fuse with side function
RU2496095C1 (en) * 2012-03-15 2013-10-20 Шепеленко Виталий Борисович Range finder
RU2496096C1 (en) * 2012-03-15 2013-10-20 Шепеленко Виталий Борисович Target contact-type laser transducer
RU2496094C1 (en) * 2012-03-15 2013-10-20 Шепеленко Виталий Борисович Laser range finder
RU2496093C1 (en) * 2012-03-15 2013-10-20 Шепеленко Виталий Борисович Target contact-type laser transducer
RU2497071C1 (en) * 2012-03-15 2013-10-27 Шепеленко Виталий Борисович Optical range finder
RU2497070C1 (en) * 2012-03-15 2013-10-27 Шепеленко Виталий Борисович Jet missile range finder
RU2497073C1 (en) * 2012-03-15 2013-10-27 Шепеленко Виталий Борисович Optical unit
RU2497069C1 (en) * 2012-03-15 2013-10-27 Шепеленко Виталий Борисович Target detection optical unit
RU2497072C1 (en) * 2012-03-15 2013-10-27 Шепеленко Виталий Борисович Jet missile target sensor
RU2498206C1 (en) * 2012-03-15 2013-11-10 Шепеленко Виталий Борисович Device for determining optimum moment of ammunition blasting
RU2498205C1 (en) * 2012-03-15 2013-11-10 Шепеленко Виталий Борисович Optic target sensor
RU2498207C1 (en) * 2012-03-15 2013-11-10 Шепеленко Виталий Борисович Device for blasting ammunition at specified distance from target
RU2498208C1 (en) * 2012-03-15 2013-11-10 Шепеленко Виталий Борисович Optic unit of non-contact detonating fuse for ammunition
RU2500979C2 (en) * 2012-03-15 2013-12-10 Шепеленко Виталий Борисович Jet projectile fuse optical unit

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2456535C1 (en) * 2011-02-15 2012-07-20 Николай Евгеньевич Староверов Staroverov hollow-charge shell (versions)
RU2479825C1 (en) * 2011-11-07 2013-04-20 Федеральное государственное унитарное предприятие "Российский Федеральный ядерный центр - Всероссийский научно-исследовательский институт экспериментальной физики" - ФГУП "РФЯЦ-ВНИИЭФ" Precision shell fuse with side function
RU2497073C1 (en) * 2012-03-15 2013-10-27 Шепеленко Виталий Борисович Optical unit
RU2496096C1 (en) * 2012-03-15 2013-10-20 Шепеленко Виталий Борисович Target contact-type laser transducer
RU2496094C1 (en) * 2012-03-15 2013-10-20 Шепеленко Виталий Борисович Laser range finder
RU2496093C1 (en) * 2012-03-15 2013-10-20 Шепеленко Виталий Борисович Target contact-type laser transducer
RU2497071C1 (en) * 2012-03-15 2013-10-27 Шепеленко Виталий Борисович Optical range finder
RU2497070C1 (en) * 2012-03-15 2013-10-27 Шепеленко Виталий Борисович Jet missile range finder
RU2496095C1 (en) * 2012-03-15 2013-10-20 Шепеленко Виталий Борисович Range finder
RU2497069C1 (en) * 2012-03-15 2013-10-27 Шепеленко Виталий Борисович Target detection optical unit
RU2497072C1 (en) * 2012-03-15 2013-10-27 Шепеленко Виталий Борисович Jet missile target sensor
RU2498206C1 (en) * 2012-03-15 2013-11-10 Шепеленко Виталий Борисович Device for determining optimum moment of ammunition blasting
RU2498205C1 (en) * 2012-03-15 2013-11-10 Шепеленко Виталий Борисович Optic target sensor
RU2498207C1 (en) * 2012-03-15 2013-11-10 Шепеленко Виталий Борисович Device for blasting ammunition at specified distance from target
RU2498208C1 (en) * 2012-03-15 2013-11-10 Шепеленко Виталий Борисович Optic unit of non-contact detonating fuse for ammunition
RU2500979C2 (en) * 2012-03-15 2013-12-10 Шепеленко Виталий Борисович Jet projectile fuse optical unit

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