RU2465542C1 - Head part of volley fire rocket system - Google Patents

Abstract

FIELD: weapons and ammunition.

SUBSTANCE: head part comprises a body and a bottom. A cylindrical container is installed in the body with a gap and is filled with a liquid filler based on oil products. The body is fixed with the container by its front end. Inside the container there is a device to sprinkle and ignite the filler. The device for sprinkling and igniting the filler comprises a shell and a propellant charge, and is arranged along the longitudinal axis of the container. The container with the liquid filler with its rear end is fixed with the shell of the filler sprinkling and igniting device, which in its turn is fixed in the rear bottom of the head part. The shell of filler sprinkling and igniting device is arranged of alternate thickness from δ_min to δ_max, where the ratio of thicknesses δ_min/δ_max makes (0.05…0.3). The largest thickness of the shell is arranged in the area of the container front end.

EFFECT: higher combat effectiveness of an ammunition head part.

1 dwg

Description

The invention relates to the field of rocket technology, namely to rockets (PC) multiple launch rocket systems.

The object of the invention is the warhead (warhead) of a multiple launch rocket of enhanced combat effectiveness, equipped with a liquid filler based on petroleum products.

Multiple launch rocket systems (MLRS) are successfully used to combat many area targets. High efficiency of defeating areal targets is achieved by conducting volley fire, which allows for a short time to deliver a massive blow with a large number of shells, and due to the large mass of the payload located in the head part, which can cause significant damage over a large area.

Providing a large area of destruction with one MLRS shell is possible in various ways, one of which is the use of multiple launch rockets with warheads equipped with a liquid filler based on petroleum products. Thus, a variant of the head of a rocket projectile is known, which is a tank-shell equipped with a liquid filler based on petroleum products and a device for spreading and igniting the filler with a body in the form of a thin-walled cylindrical cup mounted along the longitudinal axis of the head part (RF patent No. 2174670), adopted authors for the analogue.

The objective of this technical solution was to develop a warhead equipped with a liquid filler and a device for its spreading and ignition, which allows to increase the effectiveness of fire damage. The disadvantage of this design is the impossibility of its operation at high supersonic flight speeds, since in this case the head shell is subject to intense aerodynamic heating, as a result of which the temperature of the liquid filler is unacceptably increased, which in turn can lead to premature detonation of the head.

Common features with the head part proposed by the authors are the presence in the design of the analog of the head part housing, a liquid filler based on petroleum products and a device for spreading and igniting the filler mounted along the longitudinal axis of the head part.

The head part is also known according to the patent of the Russian Federation No. 2357197, which is accepted by the authors as a prototype. This head part includes a housing equipped with a liquid filler, a container placed in the head housing with a gap and fastened with a front end to it, and a device for spreading and igniting the filler, consisting of a thin-walled shell and propelling charge, placed along the longitudinal axis of the head. In the body of the head part, on the side facing the propulsion system PC, there is a rear bottom, which can be either an element of the head part or an element of the propulsion system.

The objective of this technical solution was to create a warhead with increased high-explosive efficiency for high-speed supersonic missiles.

Common features with the head part proposed by the authors are the presence in the prototype of the case of the head part with a rear bottom, mounted in the case with a gap, fastened with it by the front end of the container with liquid filler based on petroleum products and placed inside the container along its longitudinal axis of the device for spreading and igniting the filler, consisting of a shell and a propellant charge.

The head part, adopted for the prototype, operates as follows. When fired from a directing combat vehicle, a missile equipped with a liquid-filled warhead makes a flight along a ballistic trajectory with high supersonic speeds. During movement, the rocket body experiences intense aerodynamic heating. To exclude premature detonation of the liquid filler due to its aerodynamic heating, it is placed in a cylindrical container installed in the body of the head part with a gap and thereby insulated from the heated wall of the body of the head part. When a missile approaches the target, it is defeated due to the operation of the warhead. In this case, the propellant charge of the spreading device and the ignition of the filler are ignited, as a result of which the container body and the head part are destroyed, and the liquid filler is scattered and ignited. However, this design scheme of the warhead does not allow the fulfillment of modern requirements for the accuracy of delivery of ammunition to the target. This is due to the fact that the design of this type of head parts provides for cantilever fastening of the container with liquid filler at the front end. In this case, the container has a significant elongation characteristic for the warheads of MLRS shells, and its rear end can make free transverse vibrations under the influence of alternating transverse aerodynamic and vibration loads arising during the movement of the projectile along the trajectory. The result of the occurring free transverse vibrations of the liquid-filled container is an unpredictable change in the inertial-mass eccentricity of the head part and the projectile as a whole, which negatively affects the accuracy and accuracy of fire. In addition, when the shell of the device for spreading and igniting the filler in the form of a thin-walled cylinder of constant thickness, the ejection of the entire mass of liquid filler, when the propellant is ignited, occurs almost simultaneously, which does not provide the optimal concentration of filler in the resulting fine mixture with atmospheric oxygen, as a result which decreases the energy of combustion of the filler and, accordingly, the effectiveness of the use of ammunition.

составляет (0,05…0,3), причем наибольшая толщина оболочки располагается в районе переднего торца контейнера.In contrast to the prototype, in the head part of a multiple launch rocket projectile containing a body with a rear bottom, a cylindrical container filled with a liquid filler based on petroleum products, and mounted inside the container along its longitudinal axis, mounted in the case with a gap and fastened with the front end to it, spreading and igniting the filler, consisting of a shell and a propellant charge, a container with a liquid filling the rear end is attached to the shell of the device for spreading and igniting the floor rer, which in turn is secured to the rear bottom of the head portion and the sheath spreading apparatus and ignition filler is formed of variable thickness of δ _min to δ _max, wherein the thickness ratio

is (0.05 ... 0.3), and the largest shell thickness is located in the region of the front end of the container.

This allows us to conclude that there is a causal relationship between the totality of existing features of the claimed technical solution and the achieved technical result.

The objective of the invention is the creation of the head part of a multiple launch rocket shell equipped with a liquid filler based on petroleum products, which has increased combat efficiency by increasing the accuracy of the delivery of ammunition to the target and optimizing the dispersion zone of the filler and its concentration in the resulting finely divided combustible mixture with oxygen.

составляет (0,05…0,3), причем наибольшая толщина оболочки располагается в районе переднего торца контейнера.The specified technical result is achieved by the fact that in the head part of a multiple launch rocket projectile containing a body with a rear bottom, a cylindrical container filled with a liquid filler based on petroleum products, and mounted inside the container along its longitudinal axis, mounted in the body with a gap and fastened with its front end a device for spreading and igniting a filler, consisting of a shell and a propellant charge, according to the invention, the container with the liquid filler with the rear end is attached to the shell a device for spreading and igniting the filler, which, in turn, is fixed in the rear bottom of the head part, and the shell of the device for spreading and igniting the filler is made of variable thickness from δ _min to δ _max , where the ratio of thicknesses

is (0.05 ... 0.3), and the largest shell thickness is located in the region of the front end of the container.

A new set of structural elements, as well as the presence of connections between the parts of the warhead of a multiple launch rocket allow, in particular, by:

- fastening the container to the shell of the device for spreading and igniting the filler, which in turn is fixed in the rear bottom of the head part, to exclude the possibility of free transverse vibrations of the container with liquid filler inside the body of the head part, thereby significantly reducing the inertial mass eccentricity of the head part and the projectile overall, thereby improving the accuracy of the delivery of the warhead to the target. When fixing the container with the liquid filler cantilever along the front end, during the flight, free transverse vibrations of the container may occur relative to the body of the head part under the action of alternating transverse overloads and vibrations. The amplitude of the oscillations that occur largely depends on the length of the cantilevered container (the longer the length, the greater the amplitude of the oscillations). To ensure high combat efficiency of a missile equipped with a liquid filler, it is advisable to have a warhead with a large relative elongation (up to 12 calibers, see, for example, Patent No. 2154799). This allows you to place the maximum payload mass in a given caliber. Moreover, the liquid filled container also has a large elongation. When the container is cantilevered along the front end, its rear end can oscillate with a sufficiently large amplitude (up to 0.07 caliber). Such fluctuations lead to an unpredictable change in the inertial mass eccentricity of the head and the projectile as a whole. In addition, the design of the head parts of this type provides for the presence of an air cavity in a container with a liquid filler, necessary to compensate for the thermal expansion of the filler (see, for example, RF patents No. 2174669 and No. 2357193). This circumstance allows the liquid filler to move inside the container during oscillations, thereby further increasing the inertial mass eccentricity, and if a certain critical value of the oscillation amplitude is exceeded, it can lead to a hydrodynamic shock, which entails deformation, or premature destruction of the container and the head the process of movement along the trajectory. The design of the head part, in which the container with liquid filler is fastened with the front end to the body of the head part, and the rear end with the shell of the device for spreading and igniting the filler, which in turn is fixed in the rear bottom of the head part, allows for reliable fastening of the container, eliminating the possibility of occurrence its transverse vibrations under the action of alternating transverse aerodynamic overloads and vibrations, which can significantly reduce the value of inertial mass eccentricity of the head and the projectile as a whole, associated with the possible movement of the container inside the body of the head and the movement of liquid filler inside the container. This circumstance, in turn, ensures reliable operability of the structure and high accuracy of the delivery of the warhead to the target.

составляет (0,05…0,3), и выполнения наибольшей толщины оболочки в районе переднего торца контейнера, обеспечить в процессе срабатывания головной части разбрасывание жидкого наполнителя с образованием облака мелкодисперсной смеси в наибольшем объеме с оптимальной концентрацией жидкого наполнителя и кислорода воздуха, тем самым достигнуть максимальной энергетики сгорания наполнителя и увеличить зону поражения, а следовательно, и боевую эффективность. При выполнении устройства разбрасывания и воспламенения наполнителя с оболочкой, имеющей постоянную толщину стенки, в процессе воспламенения метательного заряда происходит ее разрушение по всей длине за короткий промежуток времени. В результате этого, под действием избыточного давления продуктов сгорания, происходит одновременное по всей длине разрушение стенок корпуса контейнера и головной части, жидкий наполнитель выбрасывается в атмосферу, где, смешиваясь с кислородом воздуха, образует облако мелкодисперсной горючей смеси, которая воспламеняется от контакта с продуктами сгорания метательного заряда. Форма облака мелкодисперсной смеси близка к цилиндрической и имеет длину, приблизительно равную длине контейнера с жидким наполнителем. При этом концентрация жидкого наполнителя в образовавшемся облаке оказывается выше, а концентрация кислорода ниже оптимальной, что не обеспечивает максимальной энергетики сгорания жидкого наполнителя. Увеличение концентрации кислорода в образующемся облаке мелкодисперсной смеси возможно путем увеличения размеров облака (его диаметра или длины). Увеличение диаметра облака возможно путем увеличения скорости разбрасывания жидкого наполнителя, но для этого необходимо применение более мощного метательного заряда в устройстве разбрасывания и воспламенения, что соответственно приведет к увеличению габаритов и массы этого устройства и уменьшению массы жидкого наполнителя при сохранении общих габаритов и массы головной части. В результате этого увеличения боевой эффективности головной части, несмотря на оптимизацию процесса сгорания жидкого наполнителя, не происходит. Увеличение длины облака возможно путем увеличения времени его формирования за счет растянутого во времени процесса разрушения корпуса головной части и контейнера в процессе движения по траектории. Выполнение конструкции устройства разбрасывания и воспламенения наполнителя с оболочкой переменной толщины позволяет обеспечить последовательное разрушение корпуса головной части и контейнера. В этом случае при воспламенении метательного заряда в устройстве разбрасывания и воспламенения наполнителя, разрушение его оболочки будет происходить последовательно, от участка стенки с наименьшей толщиной (δ_min) до участка стенки с наибольшей толщиной (δ_max). Связано это с тем, что для разрушения стенок оболочки, имеющих большую толщину, требуется большее избыточное давление продуктов сгорания метательного заряда, на достижение которого требуется больший промежуток времени. Так как головная часть в процессе разрушения от действия избыточного давления продуктов сгорания метательного заряда устройства разбрасывания и воспламенения наполнителя движется по траектории в направлении цели, то разрушение необходимо начинать с заднего торца контейнера. Следовательно, устройство разбрасывания и воспламенения наполнителя должно иметь оболочку с наименьшей толщиной стенки в районе заднего торца и наибольшей толщиной в районе переднего торца контейнера. При этом за счет движения головной части по траектории она за время разрушения преодолевает расстояние, способное на 20-30% увеличить длину зоны формирования облака мелкодисперсной горючей смеси. Минимальная толщина стенки оболочки устройства разбрасывания и воспламенения наполнителя (δ_min) выбирается из конструктивных соображений и условия обеспечения запаса прочности под воздействием осевых и поперечных полетных перегрузок. Максимальная толщина стенки выбирается исходя из условия обеспечения необходимого времени разрушения корпуса головной части. При этом должно соблюдаться соотношение отношение

. Увеличение соотношения

, как показывает экспериментальная практика, является нецелесообразным, так как время разрушения корпуса головной части становится очень мало и головная часть за это время не успевает сколь-либо существенно продвинуться по траектории. В результате этого ожидаемый положительный эффект незначителен. Уменьшение соотношения

приводит к чрезмерному увеличению времени разрушения корпуса головной части, в результате чего положительный эффект исчезает, так как происходит снижение концентрации жидкого наполнителя в образующейся мелкодисперсной смеси, ведущее к снижению энергетики ее сгорания. Кроме того, чрезмерное увеличение максимальной толщины стенки оболочки (δ_max) ведет к уменьшению массы жидкого наполнителя, размещенного в контейнере, при соблюдении общих габаритно-массовых параметров головной части. Оба этих обстоятельства препятствуют повышению боевой эффективности рассматриваемого боеприпаса.- shells of the device for spreading and igniting a filler of variable thickness from δ _min to δ _max , where the ratio of thicknesses

is (0.05 ... 0.3), and of the largest shell thickness in the region of the front end of the container, to ensure the spread of the liquid filler with the formation of a cloud of finely dispersed mixture in the largest volume with the optimum concentration of the liquid filler and air oxygen during the operation of the head part; to achieve maximum energy of combustion of the filler and to increase the affected area, and, consequently, combat effectiveness. When performing a device for spreading and igniting a filler with a shell having a constant wall thickness, in the process of ignition of a propellant charge, it is destroyed along its entire length in a short period of time. As a result of this, under the influence of excess pressure of the combustion products, the walls of the container body and the head part are simultaneously destroyed along the entire length, the liquid filler is released into the atmosphere, where, mixed with atmospheric oxygen, it forms a cloud of finely dispersed combustible mixture, which ignites from contact with the combustion products propellant charge. The cloud shape of the finely dispersed mixture is close to cylindrical and has a length approximately equal to the length of the liquid-filled container. In this case, the concentration of the liquid filler in the resulting cloud is higher, and the oxygen concentration is lower than the optimum, which does not provide the maximum energy of combustion of the liquid filler. An increase in the oxygen concentration in the formed cloud of a finely dispersed mixture is possible by increasing the size of the cloud (its diameter or length). An increase in the diameter of the cloud is possible by increasing the spreading rate of the liquid filler, but this requires the use of a more powerful propellant charge in the spreading and ignition device, which accordingly will lead to an increase in the dimensions and mass of this device and a decrease in the mass of the liquid filler while maintaining the overall dimensions and mass of the head. As a result of this increase in the combat effectiveness of the warhead, despite the optimization of the combustion process of the liquid filler, it does not occur. The increase in the cloud length is possible by increasing the time of its formation due to the process of destruction of the body of the head part and the container, which is extended over time, during the movement along the trajectory. The design of the device for spreading and igniting the filler with a shell of variable thickness allows for consistent destruction of the body of the head and container. In this case, when the propellant is ignited in the spreading and ignition device of the filler, the destruction of its shell will occur sequentially, from the portion of the wall with the smallest thickness (δ _min ) to the portion of the wall with the largest thickness (δ _max ). This is due to the fact that for the destruction of the walls of the shell having a greater thickness, requires a greater excess pressure of the products of combustion of the propellant charge, the achievement of which requires a longer period of time. Since the head part in the process of destruction from the action of excess pressure of the products of combustion of the propellant charge of the device for spreading and igniting the filler moves along the path in the direction of the target, the destruction must begin from the rear end of the container. Therefore, the device for spreading and igniting the filler should have a shell with the smallest wall thickness in the region of the rear end and the greatest thickness in the region of the front end of the container. At the same time, due to the movement of the head part along the trajectory, it overcomes the distance during destruction, capable of increasing the length of the zone of formation of the cloud of finely dispersed combustible mixture by 20-30%. The minimum wall thickness of the shell of the device for spreading and igniting the filler (δ _min ) is selected from design considerations and the conditions for ensuring the safety factor under the influence of axial and transverse flight overloads. The maximum wall thickness is selected based on the conditions for ensuring the necessary time for the destruction of the body of the head part. In this case, the ratio

. Ratio increase

As experimental practice shows, it is impractical, since the time of destruction of the body of the head part becomes very short and the head part does not have time to significantly advance along the trajectory during this time. As a result of this, the expected positive effect is negligible. Ratio reduction

leads to an excessive increase in the time of destruction of the body of the head part, as a result of which the positive effect disappears, since there is a decrease in the concentration of liquid filler in the resulting finely divided mixture, leading to a decrease in the energy of its combustion. In addition, an excessive increase in the maximum wall thickness of the shell (δ _max ) leads to a decrease in the mass of the liquid filler placed in the container, subject to the general overall weight parameters of the head part. Both of these circumstances hinder the increase in combat effectiveness of the munition in question.

The invention is illustrated in the drawing, where figure 1 shows a General view of the head of a multiple launch rocket with a container loaded with liquid filler based on petroleum products, and a device for spreading and igniting the filler.

The head part consists of a body (1) with a rear bottom (2) installed with a gap in the body (1) of a cylindrical container (3) filled with liquid filler based on petroleum products (4) and a device for spreading and igniting the filler (5). A cylindrical container (3) with liquid filler (4) is cantilevered with its front end to the shell of the housing (1). Inside the container (3), along its longitudinal axis, a device is installed for spreading and igniting the filler (5), consisting of a shell (6) and a propelling charge (7). The shell (6) of the device for spreading and igniting the filler (5) is fastened to the rear end of the container (3) and the rear bottom (2) of the head part. Such fastening allows avoiding oscillations of the container (3) with liquid filler (4) under the influence of alternating transverse aerodynamic overloads and vibrations. The device for spreading and igniting the filler (5) consists of a shell (6) having a variable thickness from δ _min to δ _max and a propellant charge (7), designed to create the excess pressure necessary to destroy the body (1) and container (3), spreading liquid filler (4) and igniting it.

The proposed head part works as follows. When the head part in the projectile moves along the trajectory, alternating transverse aerodynamic and vibration loads act on it. Under the influence of these forces, a container (3) with a liquid filler (4), mounted in the housing (1) of the head, tends to oscillate in the transverse plane. The fastening of the container (3) with the shell (6) of the spreading and ignition device of the filler (5), which, in turn, is fixed in the rear bottom (2) of the head part, allows to minimize vibrational processes, thereby significantly reducing the inertial mass eccentricity of the head part and the projectile as a whole. When approaching the target, the propellant is ignited (7) in the scattering and ignition device of the filler (5), as a result of which, under the influence of excess pressure of the combustion products, its shell (6), container body (3) and body (1) are destroyed head part. The liquid filler (4) is released into the atmosphere, where it mixes with atmospheric oxygen and forms a finely dispersed mixture, which ignites from the products of combustion of the propellant charge (7). At the same time, due to the implementation of the shell (6) of the device for spreading and igniting the filler (5) of variable thickness from δ _min to δ _max, its destruction stretches in time and proceeds gradually from the wall with the minimum thickness to the wall with the maximum thickness. As a result of this, the warhead manages to advance along the trajectory a certain distance. The device for spreading and igniting the filler (5) is installed in the container body (3) in such a way that the largest thickness of the shell (6) is in the region of the front end of the container (3). This installation method allows for the consistent destruction of the body of the head from the rear bottom to the front, which leads to an increase in the length of the resulting cloud of finely dispersed mixture. The increase in the cloud length of the finely dispersed mixture makes it possible to ensure the optimal concentration of filler and oxygen in it in order to obtain the maximum energy of their combustion, which in turn allows to increase the efficiency of the use of warheads of this type.

The indicated positive effect is confirmed by the large volume of bench experiments and full-scale flight tests of rockets equipped with warheads made in accordance with the proposed invention.

Currently, development of working design documentation is underway, serial production of the head parts of the proposed design is planned.

Claims (1)

The head part of a multiple launch rocket projectile comprising a body with a rear bottom, a cylindrical container filled with a liquid filler based on petroleum products, mounted in a housing with a gap and fastened with the front end thereof, and a device for spreading and igniting the filler placed inside the container along its longitudinal axis, consisting from the shell and the propellant charge, characterized in that the container with the liquid filler with the rear end is attached to the shell of the spreading and ignition device la, which in turn is secured to the rear bottom of the head portion and the sheath spreading apparatus and ignition filler made of variable thickness δ _min to δ _max, wherein the thickness ratio

is (0.05 ... 0.3), and the largest shell thickness is located in the region of the front end of the container.