WO2023203440A1

WO2023203440A1 - Warhead

Info

Publication number: WO2023203440A1
Application number: PCT/IB2023/053747
Authority: WO
Inventors: Sergey Zonenko; Veniamin ZONENKO
Original assignee: Veniamin ZONENKO; GELDKE, Olga; GULBINAS, Rytis; UAB "Bonarma"
Priority date: 2022-04-21
Filing date: 2023-04-12
Publication date: 2023-10-26
Also published as: LT6958B; LT2022516A

Abstract

A shaped charge warhead or a shaped charge with fragmentation warhead of caliber from 75 mm to 85 mm can be used in rockets, grenade launchers, and artillery systems. The warhead comprises a body, a safety and arming mechanism, an explosive charge, a waveshaper, a fairing, and a liner, wherein the outer surface of the liner, adjoining to the explosive, and the inner surface of the liner are made in the form of rotation surfaces. The generatrix of the inner surface is made in the form of a line without breaking points, located inside the figure formed by small arcs of two circles passing through the ends of the line segment connecting the base of the liner with the top, having radii equal to two and a half lengths of the specified segment. To increase the armour penetration, the liner thickness and the opening angle of the outer surface (for the special case of a cone) are correlated with the opening angle of the inner surface and the properties of the explosive used, which are determined by its composition and density.

Description

WARHEAD TECHNICAL FIELD The invention relates to shaped charge or shaped charge with fragmentation ammunition, in particular, to shaped charge warheads or shaped charge with fragmentation warheads of caliber from 75 mm to 85 mm, which are designed to destroy armoured targets with a shaped charge action and unarmoured targets with a fragmentation action, if a fragmentation part is present. BACKGROUND ART Unguided aircraft rockets, abbreviated as UAR, caliber 80 mm, are the most common aircraft rockets. The UAR consists of two parts: a 78 mm caliber warhead and an 80 mm caliber rocket engine. The following modifications of the UAR caliber 80 mm with a shaped charge with fragmentation action are known: S-8, S-8A, S-8M, S-8KO, and S-8KOM. On the basis of the UAR, guided aircraft rockets are being developed, wherein the rocket is aimed at the target using laser guidance. UAR S-8 can also be used from ground launch blocks. Thus, the historically established name "unguided aircraft rocket" does not reflect all the possibilities of using such rockets. A tandem-charge warhead S-8T was designed to destroy armoured vehicles equipped with reactive armour, with two charges: the main charge and the precursor to remove the reactive armour. A technical solution of the warhead (Unguided aircraft rocket with tandem shaped charge. Patent RU2371667C1. Ashurkov A.A. et al., published 2009-10-27) is known, which also has main and additional charges. The present invention relates to both the main and additional charges in warheads with a tandem scheme. There is UAR "Medusa" with a shaped charge warhead of 81 mm caliber, based on Swiss- Italian rockets of the SNORA and SURA families. Also known is the Chinese Norinco PF-89 disposable grenade launcher. The launch container is used to shoot a rocket-propelled grenade with an 80 mm HEAT warhead. The widely used RPG-7 hand-held anti-tank grenade launcher is used mainly for firing over-caliber grenades and can be loaded, among other things, with warheads of caliber from 75 mm to 85 mm. There are also a number of grenade launchers and artillery systems designed to launch warheads of caliber from 75 mm to 85 mm. There is a 9-GZh-4421 warhead of the S-8 KOM unguided aircraft rocket (Sychev A.I., Martirosyan V.G., Pereskokov V.A. Unguided aircraft rockets of 80 mm caliber, 2019, pp.19– 21, prototype). It consists of the following parts: a body, closed on one side with a protective baffle plate, an explosive charge, an inert waveshaper, a copper liner, a fairing. The warhead is equipped with a V-5KP1 fuze, consisting of a safety and arming mechanism, abbreviated as SAM, and a piezoelectric generator. The electric connection between them is provided by a conductor inserted into the waveshaper, a conductive cone, and an insulating clamping ring. The piezoelectric generator converts the mechanical energy of the rocket hitting the target into the electric energy required to trigger the SAM. The body is a thin-walled aluminum tube, expanding in the head part, having threads at both ends, which serve to connect the body with the fairing and the rocket part on the sealant of the body. A groove is made in the head part inside the body, into which an insulating polyethylene ring is inserted, at the place where the base of the liner approaches the wall of the body. The fairing serves to ensure good aerodynamic properties of the rocket and the required standoff distance between the target and the base of the liner at the moment of impact on the target, and is also a link in the external electric circuit. Besides the fuze, which consists of a head piezoelectric generator and SAM, base fuzes are also used, driven by inertial strikers, springs, or other methods. A small-sized base fuze is known (Base fuze. Patent RU2125706C1. Andrejkin P.V. et al., published 1999-01-27), which has high sensitivity and high speed of action in contact with the target. The fuze contains a body, a firing gear in the form of a tip, a counter-safety spring, a spherical inertial body in a conical bottom section and a cylindrical section, a safety system, and a firing circuit. In addition, the fuze can be fitted with a remote cocking mechanism and a self-destruct mechanism that initiates the charge if, for some reason, the fuze fails to fire on contact with the target or due to other abnormal functioning. The fragmentation part of the UAR warhead usually contains pre-fragmented elements outside the body in the form of rings, bushings, or spirals. These elements are put on a smaller diameter of the body and are fixed with a clamping nut. In the 9-GZh-4421 warhead, the pre- fragmented elements are made in the form of a spiral of a steel profile strip with notches to ensure crushing into fragments weighing about 3 g. Shaped charge with fragmentation warheads for UAR S-8 preferably use A-IX-10 or A- IX-1 explosive with a detonation velocity from 8.3 km/s to 8.45 km/s. A waveshaper inside the explosive charge serves to spread the detonation wave to the walls of the body. In the 9-GZh-4421 warhead, adopted as the prototype, the waveshaper is made of compressed material AG-4V. For it, the quantities included in the Rankine-Hugoniot relations for mass: ρ/ρ0 = D/(D – U), and momentum: P – P0 = ρ0 U D, have the following values: ρ0 = 1.79 g/cm³, ρ = 3.19 g/cm³, D = 5.95 km/s, U = 2.61 km/s, where ρ is the density (with the index "0" – ahead of the shock wave front), D is the velocity of the shock wave, U is the mass velocity of matter; the pressure is P = 27.8 GPa (Trunin R.F., Gudarenko L.F. et al. Experimental data on shock wave compression and adiabatic expansion of condensed substances, 2006, p.207). The mass of the 9-GZh-4421 warhead is 3.6 kg, the mass of the explosive is 1 kg, the number of fragments during an explosion weighing 3 g each is at least 400 pieces (Sychev A.I., Martirosyan V.G., Pereskokov V.A. Unguided aircraft rockets of 80 mm caliber, 2019, p.17). In the 9-GZh-4421 warhead, the liner is made of copper and has a shape of a hollow cone with an internal opening angle of 60° and a wall of variable thickness. A brass tube is attached to the top of the liner by flaring and soldering to transmit an electric impulse from the piezoelectric generator to the bottom part of the fuze. The possibilities of increasing the effectiveness of the warhead by correlating the design and parameters of the warhead with the properties of explosives in the technical solution adopted for the prototype are not used enough. In a traditional shaped charge, under the pressure of a detonation wave, the liner is compressed toward the charge axis, a thin metal jet is squeezed forward, and a low-velocity slug remains behind (Bazhin V.E., Dankov V.S. et al. Explosion, explosives, their application, 2008, рр.31, 34). Most of the energy of the explosion is wasted on compressing the liner rather than on the forward acceleration of the liner material. Increasing the effectiveness of shaped charge ammunition is in the following main areas: ^ improvement of explosives, ^ development of devices that affect the propagation of detonation waves, ^ the creation of more reliable fuzes with improved characteristics, ^ improvement of the physical and mechanical properties and structure of the liner material, ^ modernization of the geometrical shapes of liners, ^ upgrade in manufacture precision. Liners are usually made of copper. Modern methods of metallurgy, including powder metallurgy, the use of bimetals and metal polymers, make it possible to improve the properties and structure of the liner material in order to increase the efficiency of shaped charges. A liner is known (Cumulative charge coating. Patent RU2337307C2. Kachalin N.I. et al., published 2008-10-27), manufactured from pseudo-alloy using metal powder metallurgy method. In the case offered, the material used is pseudo-alloy of Mo-Cu-Ni with density of 9.30–9.85 g/cm³, and Cu contents of 25–60% by weight, Ni – not more than 0.8% by weight, and Mo is the rest. The material proposed for liners contributes to an increase in the penetration depth. The technical level of the design of shaped charge warheads reflects the liner (Shaped Charge Liner with Integral Initiation Mechanism. Patent No. US6026750. Carl A. Nelson, published 2000-02-22), which has a forward thin wall section and a tail end section. The content of the patent is devoted to a detailed study of the tail end section. The forward thin wall section may have various shapes. In particular, a conical, hemispherical, bell, trumpet, or tulip-shaped surface can be used. This patent does not use the ability to control the operation parameters of the shaped charge by optimizing the shape and thickness of the liner. The most widespread are conical liners. This is due to the simplicity of their manufacture and efficiency sufficient for many applications. However, efforts to modernize the shapes of liners are underway. The shape of the liner is known (Shaped Charge Liner. Patent No. US6840178B2. William R. Collins et al., published 2005-01-11), which is a combination of at least three axially aligned, substantially frusto-conical sections with different opening angles, passing into each other. The disadvantage of this shape is the presence of parallels with a break in the surface, where the conical surface with one opening angle passes to the conical surface with another angle. During explosive compression of such a liner, the liner material gathers to form thickenings or expands to form a liner breach. When thickening, the speed of the liner decreases; in the event of a liner breach, detonation products flow out to the front side, slow down the liner, and reduce the kinetic energy spent on breaking through the target. After selecting the shape of the liner, the question arises about the distribution of the thickness of the liner. There is very little scientific research on this matter in question. There are such inaccurate estimates as in the textbook (Bazhin V.E., Dankov V.S. et al. Explosion, explosives, their application, 2008, p.38), which states the following: a penetrating ability of a shaped charge depends on the material of the liner and its thickness; both the too large and too small thickness of the liner is unfavorable; thickness varies from 0.5 mm to 3 mm depending on the material, size, and design of the liner. The penetrating ability also depends on the explosive used. Explosives with the highest possible density and detonation velocity must be used. However, for the effective design of shaped charge warheads, it is necessary to have more accurate values of the liner thickness for specific conditions: the geometric shape and material of the liner, the presence or absence of a waveshaper, the composition and the density of the explosive used, on which the detonation velocity and explosion pressure depend, etc. It can be argued that for almost all existing liners of shaped charges, the thickness was found empirically by conducting plenty of experiments. This path is not only costly but also not inaccurate since it is empirically impossible to go through all theoretically possible options. New results of the theory of explosion show that the distribution of the thickness of the liner is of great importance for the operation of the shaped charge, and the explosive in the corresponding body serves only to create the pressure field necessary for throwing the liner. At the same time, even for the simplest conical shape of the liner and a linear distribution of thickness, it is difficult to find acceptable recommendations for determining the thickness and linear dependence coefficient. SUMMARY OF THE INVENTION The technical aim of the invention is to increase the armour penetration of shaped charge warheads or shaped charge with fragmentation warheads of caliber from 75 mm to 85 mm. A shape and thickness of a liner are critical to the operation of the warhead. In the present invention, the liner's shape and thickness are selected so that the trajectories of the particles of the liner curve and stretch forward, forming a cumulative extending rod. The high kinetic energy of the rod is provided by a decrease in the velocity components towards the axis of the liner and an increase in the path length of the liner particles before sticking to the rod. The problem is solved by selecting the optimal geometric shape of the liner and correlating the thickness and angles of the liner with other parameters of the warhead. Due to this, during the explosive throwing of the liner, the cumulative extending rod with high kinetic energy and a small diameter is formed, which leads to more beneficial use of the energy of the explosion and, due to this, an increase in the depth of penetration of the armoured target. This effect was theoretically predicted as a result of long-term scientific research and confirmed by several hundred explosions of experimental warheads. The result obtained is applicable in a wide range of liner opening angles, for explosives, both widely used at present and experimental ones, with different densities. The explosive used must contain at least 70% of RDX, or HMX, or HNIW (CL-20). The technical solution of the problem is as follows. A shaped charge warhead or a shaped charge with fragmentation warhead comprises a body (1) with an outer diameter in the head part from 75 mm to 85 mm, a safety and arming mechanism (2), an explosive charge (3) with a hollow cavity in the head part, a waveshaper (4), a fairing (6). A liner (5) with a density of 8 g/cm³ to 10 g/cm³ is located in the hollow cavity of the charge. Figs. 1–8 show different examples of implementation, in which the same numbers represent the same elements. The safety and arming mechanism (2) can be a self-sufficient base fuze or a part of a head- bottom fuze operating in conjunction with a piezoelectric generator (10). In the second case, to provide an electric circuit between the SAM (2) and the piezoelectric generator (10), it is possible to use a conductor (7) inserted into the waveshaper (4), a conductive cone (8), or an electric cable, or other elements of the electric circuit; the conductive cone (8) is pressed against the liner (5) by an insulating clamping ring (9). The outer surface of the liner, adjoining to the explosive, and the inner surface of the liner are made in the form of rotation surfaces with a common axis, with a wide open edge, called the base, and a narrow part on the other side, called the top (Figs.18–20). The opening angle α at the base, necessary for correlation with the parameters of the liner, is taken between the tangents to two opposite meridians of the inner surface at the base. The inner diameter D of the liner base is from 60 mm to 75 mm. On the parallel of the outer surface at a distance l from the base along the axis of the liner, the thickness of the liner δ_l is set. The value of l is in the range: 2 mm ≤ l ≤ 8 mm (Figs.21–23). The necessary features of a technical solution are the following: ^ the generatrix of the inner surface of the liner is made in the form of a line, located inside the figure (pos. 22, Fig. 24), formed by small arcs of two circles passing through the ends of the line segment connecting the base of the liner from the inside with the top, the beginning of the rounding of the top, the beginning a cylindrical part or another tip at its top, with centers located on opposite sides of this segment, ^ radii of these circles are equal to two and a half lengths of the segment (Fig.24), ^ a doubled angle between the segment and the liner axis is greater than 23° and less than 125°, ^ the generatrix does not have breaking points (Figs.25a–25c), ^ the thickness δ_l is in the range from 1.2 mm to 3 mm (Figs.21–23), ^ for a charge with density ρ < 1.7 g/cm³, the specified thickness is less than 2.6 mm. If there is a chamfer on the outside at the base of the liner, the thickness is taken along the normal to the inner surface so that the normal reaches the outer surface without a chamfer. In a particular case of implementation, the liner can have outer and inner surfaces in the form of side surfaces of right circular cones with different opening angles, respectively, β and α (Fig.23). To increase the armour penetration of the warhead, the liner thickness δ_l at a distance l from the base and the angle difference (β - α) (for the special case of a cone, Fig.23) are correlated with the angle of the inner surface α and the properties of the explosive used, which are determined mainly by its density ρ. The liner must be thin enough so that the trajectories of the particles of the liner are curved and stretched forward. But at the same time, the liner must have a sufficient thickness in order not to break under the action of pressure from the detonation products, so that there is no counterpressure of gases breaking through the liner. To do this, the range of angles α is divided into intervals of 10°. The explosive density range is divided into 4 intervals. The first interval, with a density from 1.6 g/cm³ to 1.7 g/cm³, mainly includes RDX-based substances. The second interval, with a density from 1.7 g/cm³ to 1.8 g/cm³, includes substances based on HMX with various additives. In the third interval, with a density from 1.8 g/cm³ to 1.9 g/cm³, there are substances based on HMX with increased detonation velocity and explosion pressure. The fourth interval, with a density from 1.9 g/cm³ to 2 g/cm³ – substances based on HNIW (CL-20) (Table 1). For each interval, the values of δ_l are given; for the conical liner, also the angle difference (β - α) are given (Fig.23). Metals (including bimetals), metal alloys (including powder and pseudo-alloys), as well as metal polymers can be used as liner material. An anti-corrosion coating is allowed. The preferred option is when the liner is made of copper with a total mass fraction of impurities of less than 0.1%. The liner thickness along any parallel of the inner or outer surface is determined along the normal to the inner surface. The preferred option is when the liner thickness along any parallel of the inner or outer surface has a tolerance of less than ±0.05 mm. The liner may have elements for installation and/or elements for initiation. In addition to the described shaped charge part, the warhead may have a fragmentation part. In the following, seven possible variants of the fragmentation part are given and illustrated as implementation examples (Figs.9–16). Other features and advantages of the present invention will become apparent to those skilled in the art from the description of the drawings, in which the same numbers represent the same elements, examples of the invention, theoretical justification, experimental evaluation of the effectiveness of the proposed technical solution and the claims. BRIEF DESCRIPTION OF THE DRAWINGS Fig.1 depicts the external view of a typical shaped charge with fragmentation warhead for an 80 mm caliber unguided aircraft rocket. Figs. 2–5 depict the partial sections for some embodiments of the present invention. Fig. 4 depicts a warhead with a head-bottom fuze, operating in conjunction with a piezoelectric generator, Fig.5 depicts a warhead with a self-sufficient base fuze. Figs. 6, 7 depict the appearance and partial section of a shaped charge warhead without a fragmentation part and a head piezoelectric generator; it is designed for 81 mm caliber rockets, for example, UAR "Medusa". Fig.8 depicts a shaped charge warhead, which can be a warhead of a rocket-propelled anti-tank grenade for an anti-tank grenade launcher. Fig.9 depicts a warhead layout, in which the pre-fragmented elements are made in the form of rings, bushings, or spirals, attached on a smaller diameter of a body. Fig.10 depicts similar pre-fragmented elements which are located inside a body. Fig.11 depicts ready-made damaging elements inside a body. Fig. 12 depicts a part of a body with thickened walls with pre-fragmentation in the form of transverse or oblique notches and cuts on the inside of the body. Fig. 13 depicts a part of a body with thickened walls with similar pre-fragmentation on the outside of the body. Fig.14 depicts a part of a body with a flexible sleeve with ready-made damaging elements. Fig. 15 depicts a part of a body with dents made according to some periodic pattern over the entire inner surface. Fig. 16 depicts a combination of two of the above options of pre-fragmented elements. In addition, in Fig.16, the symbol D_standoff indicates the standoff distance. Fig.17 depicts the main forms of waveshapers used in shaped charge ammunition. Figs.18–20 depict various forms of liners made according to the present invention. Figs.21–23 depict the liner schemes, with the opening angle of the inner surface α, the opening angle of the outer surface β (for a conical liner, Fig.23), the inner diameter of the liner base D; the liner thickness δ_l is indicated at a distance l from the base of the liner. Fig. 24 depicts a scheme of the construction of the generatrix of the inner surface; there are shown a line segment of length L, along which the generatrix is built, and the angle γ/2 between the segment and the liner axis, where the value γ may vary from 23° to 125°. Figs.25a–25c depict some examples of the inner surface. DETAILED DESCRIPTION OF THE INVENTION The shaped charge warhead has a body (1) in the form of a thin-walled shell with a cylindrical-conical surface (Figs. 2). The internal volume of the body must be sufficient to accommodate a safety and arming mechanism (2), an explosive charge (3), a waveshaper (4), and a liner (5). Based on this, the geometric design of the body is selected. The body usually has threads at both ends, connecting the body to the fairing and various means of accelerating and stabilizing the flight of the warhead. Often, to lighten the warhead, the body is made of aluminum and its alloys. Shaped charge versions of the warhead (Figs. 6–8) do not have a fragmentation part. The design of a shaped charge with fragmentation warhead (Figs. 1–5) depends on the selected version of a fragmentation part. The most common version of a body for UAR is a thin-walled hollow cylinder with two diameters (11), which has a smooth transition from one to the other diameter, with threads at both ends (Fig.9). The fragmentation part can be made of 17 steel rings, put on the smaller diameter of the body, each of which has 24 notches on the inside, which ensured the production of 408 fragments (17 ∙ 24 = 408) weighing about 3 g. A similar effect can be obtained with a steel spiral (12) or bushings with notches on the inner surface. These elements are put on the body and are fixed with a clamping nut (13). In addition, other variants of the fragmentation part can be used (Figs.10–15): ^ a body (14) and pre-fragmented elements (15) in the form of rings, bushings, or spirals inside the body, ^ a body with ready-made damaging elements (16) in the form of balls, rods, cubes, prisms, etc. inside the body; a binder, such as epoxy glue, can be used to fasten them, ^ a body (17) with thickened walls with preliminary fragmentation in the form of notches and cuts on the inner side of the body, dividing the body walls into fragments with the required mass; notches and cuts can be made along the axis of the warhead, across or at an angle, ^ a body (18) with thickened walls with pre-fragmentation in the form of similar notches and cuts on the outside of the body, ^ flexible fragmentation sleeve (19) with ready-made damaging elements (20) outside a body, ^ a body (21) with dents made according to some pattern over the entire inner surface. It is also possible to use another version of the fragmentation part or a combination of different options (Fig.16). Of these body options, there is no preferred one in terms of the functioning of the warhead. It is possible to use any of these or a combination of them. This can be done to increase the number of fragments of the required mass. In general, the choice of body implementation is determined by technological and production factors. Inside the body (1), there is an explosive charge (3), consisting of several explosive briquettes or representing a single solid element. RDX-based compositions are most often used as explosives in UAR warheads. A combined version is preferable, in which a more powerful HMX-based composition is used for the shaped charge part and RDX-based – for the fragmentation part. In all cases, the explosive must provide the necessary electric insulation. Table 1 shows the parameters of some explosives (Military Explosives. Technical Manual No. 9-1300-214, with Changes 1–4. Headquarters, Department of the Army). The explosives listed in the table, as well as other powerful explosives, have a feature – they contain at least 70% of RDX, or HMX, or HNIW (CL-20) (Pirospravka. Handbook of explosives, gunpowder and pyrotechnic compositions, 6th edition, 2012, pp.182–188). Theoretical research, numerical calculations, and experimental studies by the authors of this invention were carried out for such substances. The liner parameters proposed in the claims were developed for explosives containing at least 70% of RDX, or HMX, or HNIW (CL-20). In the head part of the explosive (3), there is a hollow cavity into which the liner (5) is pressed. In the bottom part, there is a recess for accommodating a safety and arming mechanism (2). In a rocket warhead, the bottom of the body is usually closed by a protective baffle plate. A waveshaper (4) is placed between the SAM and the liner, which spreads the detonation wave coming from the SAM to the walls of the body. This serves to create a more favorable pattern of the detonation wave inside the charge. The location of the waveshaper inside the explosive charge is determined from the condition that the distance from the cross section of the waveshaper in the wide part to the top of the liner should not exceed the diameter of the waveshaper in the wide part. If the largest diameter is preserved in some section of the waveshaper, then the cross section closest to the liner with the largest cross-sectional diameter is selected, and the distance to the top of the liner is measured from it – it should not be more than the largest diameter of the waveshaper. The shape of the waveshaper is chosen so that the detonation wave enveloping it reaches the opposite side before the shock wave passing through the material of the waveshaper. Fig. 17 shows the main forms of waveshapers used in shaped charge ammunition. For the waveshaper, inert materials can be used, for which the velocity of shock waves at a pressure equal to the pressure of the explosion is less than the detonation velocity of the explosive used. In shaped charge ammunition, brisant explosives are usually used, the detonation velocity of which ranges from 8 km/s to 9.5 km/s (Table 1). Waveshapers can be made not only from inert materials, but also from explosives with a low detonation velocity. Table 1. Parameters of some explosives Substance % Detonation velocit

25 HNIW-98 – – 98 2.00 9350 A fairing (6) has a conical or ogive shape with a thin wall. A conductive cone (8) connects the head piezoelectric fuze to the base of the liner. In the case of using a base fuze without a head piezoelectric generator, the conductive cone is not used, and the thickness of the fairing walls increases (Figs.5, 7). The length of the fairing determines the standoff distance (Fig.16) between the target and the liner at the moment of impact on the target. Ensuring the correct standoff distance is essential to the warhead effectiveness. Base fuzes usually have a high speed of action. In this case, the standoff distance is equal to the distance from the base of the liner to the top of the head piezoelectric generator. Fuzes with a piezoelectric generator have a delay time (Markovsky V., Prikhodchenko I. Unguided rockets of the S-8 type. M-Hobby, 2013, No.9 (148), p.46). Although it is very small (20–30 microseconds), nevertheless, the delay time leads to a decrease in the standoff distance between the target and the liner at the moment the explosive charge is detonated. The flight speed of a rocket launched from a launch vehicle is equal to the sum of the speed of the carrier from which the launch is made and the speed at which the rocket itself can be accelerated. The maximum speed of modern attack helicopters is about 300 km/h, and for fighter aircrafts, the speed of sustainable flight only begins from this value. The cruising speed of fighter aircrafts is much higher. For example, for the MiG-29: about 850 km/h. If we also take into account the own speed of the rocket, about 600 m/s, and the conversion factor from km/h to m/s (1 km/h = 0.278 m/s), then the standoff distance between the target and the liner at the moment of impact can decrease by 16–24 mm (for fighter aircrafts), by 13–20 mm (for helicopters) or by 12–18 mm if fired from a ground launcher. Calculation and experimental studies of the authors of this invention showed that the standoff distance between the target and the base of the liner at the moment of explosion of the explosive charge should be about 0.5∙L_pen, where L_pen is the average penetration depth of the armoured target. This rule is valid for warheads with different explosives and liners of different shapes and thicknesses. Tests of the proposed warheads showed that when using explosives of A-IX-1 type, the warhead penetrates about 450 mm at the opening angle of the conical liner α = 70° and about 470 mm at the opening angle α = 40° (Tables 3 and 4). Therefore, the standoff distance should be approximately 225 mm for the warhead with the liner at the opening angle of α = 70°. When designing warheads, it is necessary to add 16–24 mm (for fighter aircrafts), compensating for the delay in the operation of the bottom detonator, and another 10 mm, for the opening angle of about α = 40°. Thus, the distance from the base of the liner to the top of the head piezoelectric generator should be 240–250 mm, and for small opening angles of the liner: 250–260 mm. To ensure the required dimensions of the rocket, deviations from these distances are allowed, usually downward, but not more than 10%. As shown by numerous tests of various shaped charge ammunition, the above dependence of the optimal standoff distance on armour penetration is quite accurate. More correctly, it can be written as follows: 0.45∙L_pen ≤ D_standoff ≤ 0.5∙L_pen, where D_standoff is the standoff distance between the target and the liner base (Fig.16). Another important issue is the question of the dependence of the penetration depth on the opening angle of the liner α. Calculations and experiments have shown that at opening angles of the conical liner from 50° to 70°, the average penetration depth of the shaped charge with the waveshaper remains practically unchanged. And for angles less than 50°, the penetration depth increases when using one type of explosive. For a 78 mm caliber rocket warhead, the increase in armour penetration is approximately 2 mm per degree with a decrease in the opening angle in the range: 30°≤α<50°. At the same time, when designing a warhead, it is necessary to increase the standoff distance: by 1 mm with a decrease of 1°. In many cases, the use of liners with small opening angles of the conical liner is associated with practical difficulties related to the dimensions of the ammunition. But for the rocket warhead with a long body length, such liners are undoubtedly advantageous. To provide an internal electric circuit between the piezoelectric generator and the bottom part of the fuze, the conductive cone (8) is installed between the piezoelectric generator and the liner. An insulating clamping ring (9) is installed to press the cone flange against the base of the liner. A conductor (7) is attached to the top of the liner by flaring and soldering, which is inserted into the hole in the waveshaper. A fuze contact is inserted into the other end of the conductor. To ensure electric insulation, opposite the base of the liner, an annular groove is made in the body wall, into which an insulating ring, for example, made of polypropylene, is inserted. When installing a base fuze, positions (7)–(10) are not used, and the annular groove for the insulating ring is not made. The outer surface of the liner, adjoining to the explosive, and the inner surface of the liner are made in the form of a rotation surface with a common axis, with a wide open edge (the base of the liner) and a narrow part on the other side (the top of liner) (Figs.18–20). A rotation surface is a surface formed by rotating a curve around a straight line, called an axis of the surface. When rotating about the axis, the curve that forms a new shape is called a generatrix. Meridians are lines of intersection of the rotation surface with planes passing through the axis of rotation. Parallels are lines of intersection of the surface with planes orthogonal to the axis of the surface. At a distance l from the base along the axis of the liner in the parallel of the outer surface, the thickness δ_l is set. The value of l is in the range: 2 mm ≤ l ≤ 8 mm (Figs.21–23). The liner thickness along any parallel of the inner or outer surface is determined along the normal to the inner surface and has a tolerance of less than ±0.05 mm. For the present invention, the inner diameter D of the base of the liner satisfies the condition: 60 mm ≤ D ≤ 75 mm (Figs.21–23). The generatrix of the inner surface of the liner is made in the form of a line constructed in the following way: ^ a line segment is built connecting the base of the liner from the inside with the top, the beginning of the rounding of the top, the beginning of the cylindrical part, or another tip at its top, depending on the method of making the top, ^ small arcs of two circles are drawn through the ends of the constructed segment, the centers of which are on opposite sides of the segment (Fig.24), ^ radii of these circles are equal to two and a half lengths of the specified segment, ^ a doubled angle between the segment and the liner axis is from 23° to 125°, ^ the desired line is drawn from the top to the base, located inside the figure, formed by the indicated arcs (pos.22, Fig.24), ^ the desired line should not have breaking points (Figs.25a–25c). For any opening angle α at the base, the following features are met: ^ the thickness δ_l is in the range from 1.2 mm to 3 mm (Figs.21–23), ^ for a charge with density ρ < 1.7 g/cm³ the indicated thickness is less than 2.6 mm. The outer and inner surfaces of the liner can be made in the form of side surfaces of right circular cones with different opening angles (Fig. 23). A right circular cone is a cone whose base is a circle, and the orthogonal projection of the vertex onto the plane of the base coincides with the center of the circle. The side surface of a right circular cone is a special case of a rotation surface. The opening angle α of the inner surface at the base (Figs.21, 22), the opening angle β of the outer surface (for the special case of the cone, Fig. 23) and the liner thickness must be correlated with other parameters of the shaped charge. Due to the fact that the doubled angle γ may vary from 23° to 125°, and the radii of the circles are equal to two and a half lengths of the segment, the angle α can range from 0° to 148°, the angle β is slightly larger than α and ranges approximately from 0° to 150°. The liner may have a chamfer on the outside at the base of the liner. In this case, the thickness δ_l is taken along the normal to the inner surface at the point where the normal reaches the outer surface without a chamfer. An average density ρ of explosive can be determined by standard laboratory methods. The liner should have such a thickness δ_l at a distance l so that for the specified ranges of angle α and density ρ of the explosive used, the values of δ_l satisfy the conditions specified in the corresponding claims of the invention. For the case of a conical liner (Fig.23), the thickness δ_l and the difference of the opening angles of the outer and inner surfaces (β - α) must meet the relevant requirements. For example, it is required to develop a warhead charged with A-IX-10, having a density of 1.64 g/cm³, with a liner, having an inner diameter of 68 mm and an opening angle of the inner surface α = 42°. In that case, at a distance l = 5 mm from the base, the liner should have a thickness δ_l: from 1.41 mm to 2.14 mm, and the angle difference (β - α): from 1° to 1°30' (claims 12, 13). Therefore, the angle β must be from 43° to 43°30'. Under these conditions, a cumulative extending rod is formed with the maximum possible mass, high speed of the head part, uniform tension, and a small cross-sectional diameter. As a result, there is an effective transition of the explosion energy into the kinetic energy of the cumulative rod of the optimal shape, which leads to an increase in target penetration depth. Moreover, this can be achieved in a wide range of liner opening angles and for explosives with different densities. It is only necessary when designing to select the parameters of the liner in accordance with the claims of the present invention. When choosing a parameter value from a range depending on another parameter, also defined in a certain range, one should be guided by the usual rule in mathematics: if the range boundary in the domain of definitions is included in the range, then the corresponding range boundary in the function domain is also included in the range, if the range boundary is not included in the domain of definitions, then the boundary is not included in the function domain. For example, if the domain of definitions is: 1.6 g/cm³ ≤ ρ < 1.7 g/cm³, and the function domain is the range from 1.31 mm to 2.01 mm, then the boundary 1.31 mm is included in the range, the boundary 2.01 mm is not included in the range (claim 2). Theoretical estimates and control experiments have shown that when selecting a liner material, it is necessary that its density must be greater than the density of steel, which ranges from 7.7 g/cm³ to 8 g/cm³, and it is sufficient that it exceeds this density by no more than 25%. The liner can be made of copper with a density of about 8.9 g/cm³. When developing the geometric shape of the liner, it is logical to apply the Lagrangian description, which determines the parameters of the state and movement of each material particle (coordinates, velocity, etc.) at any time. For the liner having the shape of a rotation surface, the mass and the velocity of the cumulative rod element formed from some Lagrangian ring of the liner are determined by three factors: ^ the diameter of the considered Lagrangian ring, ^ the angle between the tangents to two opposite meridians of the inner surface of the ring, ^ the thickness of the liner in this place. Their influence is shown as follows: ^ an increase in diameter, without changing these other two parameters, leads to an increase in the speed of the cumulative extending rod due to an increase in the path length of the Lagrangian particles of the liner, ^ an increase in the specified angle works in the same way as increasing the diameter, ^ an increase in thickness, on the contrary, slows down the liner. At the same time, due to the large accelerations observed during the explosive throwing of the liner, even a small change in these parameters leads to significant changes in the throwing dynamics. There is a paradox of a large influence of small deviations. In view of this paradox, it is necessary to avoid breaking points on the generatrix of the rotation surface and large deviations of the shape of the liner from the basic conical one. A breaking point is a singular point of a curve at which the curve branches into which this point divides the original curve have different one-sided tangents. If the curve has no breaking points, then the tangents on one side and the other coincide at all points of the curve. Broad mathematical research, numerical calculations, and numerous experiments have made it possible to develop a principle that the best shaped charge liners must satisfy. For them, the generatrix of the inner surface of the liner should be made in the form of a line without breaking points, located inside the figure (pos.22, Fig.24), formed by small arcs of two circles passing through the ends of the line segment connecting the base of the liner from the inside with the top (the beginning rounding of the top, the beginning of the cylindrical part or another tip), having radii equal to two and a half lengths of the specified segment, the centers of which are located on opposite sides of this segment. After choosing the geometric shape of the liner, it is necessary to correlate the thickness and the opening angle of the liner with the dynamic parameters of the explosive throwing, which are determined by the composition and the density of the explosive. Coordination was carried out by calculating the explosive throwing of liners in a wide range of opening angles for explosives with different densities. The calculation results were verified experimentally. The optimal parameters of the liners were determined; the selected parameters are indicated in the relevant claims. Conical liners do not lose their relevance; they are the special case of liners specified in the present invention. Correlating the thickness, the opening angle of the inner and the outer surface with the composition and density of the explosive increases the efficiency of shaped charges with conical liners. The correct determination of these parameters makes it possible to control the parameters of the cumulative extending rod in order to increase its kinetic energy and optimize the velocity gradient and the rod diameter in different areas. Due to this, it is possible to increase the main parameter of the warhead, which is the penetration depth. A comparison of the effectiveness of the proposed warhead with the prototype was made. Warheads were produced with copper liners with an internal opening angle of 60° and a wall of ordinary variable thickness; a phlegmatized hexogen was used. Warheads of the same design were also made, but charged with a more powerful explosive Okfol-3.5 (Table 2). The effectiveness of the proposed technical solution was evaluated. There were made warheads with parameters specified in the invention and parameters different from them. To compare the proposed warheads and the prototype, new warheads with conical copper liners were made with an outer diameter of the body of 78 mm, an inner diameter of liners of 68 mm, and with different opening angles and parameters according to the invention. In tables 3–6, the liner thicknesses δ_l are given for l = 5 mm, and the index "l" is not indicated. As an explosive with a density of 1.6 g/cm³ ≤ ρ < 1.7 g/cm³, the composition A-IX-1 was used, with a density of 1.7 g/cm³ ≤ ρ < 1.8 g/cm³ – phlegmatized octogen Okfol-3.5. A set of armour plates placed close to each other was used as a target. The head piezoelectric fuze was not used. Warheads were installed perpendicular to the upper armour plate with a gap of about 20 mm between the plate and the fairing end. Such a gap imitates the real position of the warhead at the moment of detonation, taking into account the delay time of the operation of the bottom part of the fuze for the warhead with a head-bottom fuze, operating in conjunction with a piezoelectric generator. Tables 3–6 show armour penetration results for each warhead tested. The tables show the effectiveness of various warhead manufacturing options based on the average penetration depth for each option. Table 2 Test results for the ordinar rotot e (with A-IX-1) and char ed with Okfol-3.5

4 Prototype 390 5 Prototype 380

Table 3. Test results for warheads with A-IX-1 and liners with α=40° (claims 12, 13) Place b

27 α=40°, δ=2.2, (β - α)=1°40' 330 Table 4. Test results for warheads with A-IX-1 and liners with α=70° (claims 18, 19) Penetration Average Place by N

α= , = . , (β - α)= Table 5 Test results of warheads with Okfol-35 and liners with α=45° (claims 14 15)

4 α=45°, δ=1.5, (β - α)=1°30' 420 420 5 5 α=45°, δ=1.5, (β - α)=1°30' 430

Table 6. Test results of warheads with Okfol-3.5 and liners with α=70° (claims 18, 19)

12 α=70°, δ=2.1, (β - α)=1°45' 440 13 α=70°, δ=2.1, (β - α)=2° 490 470 1

From the analysis of the experiments performed, it follows that for all tested opening angles of the liners and all used explosives, the highest penetrating ability is observed in cases where both parameters of the liners, the thickness δ_l, and the angle difference (β - α), satisfy the criteria specified in the claims of the invention. Less armour penetration occurs when the thicknesses δ_l meet the required criteria, but the angle difference (β - α) does not. At the same time, in these cases, the average penetration is still greater than the average penetration of the prototype (400 mm) and the average penetration of the prototype with a more powerful explosive (420 mm). The worst results, even less than those of the prototype, are observed in cases where both liner parameters, thickness δ_l and the angle difference (β - α), do not meet the required criteria. The examples given do not exhaust the possible applications of the invention. However, they are a convincing confirmation of the effectiveness of the technical solution, which was proposed on the basis of extensive scientific research, calculations, and experiments. The experiments carried out showed the superiority of the proposed warhead options in comparison with the prototype. The invention is described in sufficient detail to comply with the provisions of the patents and to provide those skilled in the art with the information necessary to apply the new principles. However, it should be understood that the described technical solution can be implemented using other details and components without deviating from the true spirit and scope of the present invention. References 1. Unguided aircraft rocket with tandem shaped charge. Patent RU2371667C1. Ashurkov A.A. et al., published 2009-10-27. 2. Sychev A.I., Martirosyan V.G., Pereskokov V.A. Unguided aircraft rockets of caliber 80 mm, 2019. 3. Base fuze. Patent RU2125706C1. Andrejkin P.V. et al., published 1999-01-27. 4. Trunin R.F., Gudarenko L.F. et al. Experimental data on shock-wave compression and adiabatic expansion of condensed substances, 2006. 5. Bazhin V.E., Dankov V.S. et al. Explosion, explosives, their application, 2008. 6. Cumulative charge coating. Patent RU2337307С2. Kachalin N.I. et al., published 2008- 10-27. 7. Shaped Charge Liner with Integral Initiation Mechanism. Patent No. US6026750. Carl A. Nelson, published 2000-02-22. 8. Shaped Charge Liner. Patent No. US6840178B2. William R. Collins et al., published 2005-01-11. 9. Military Explosives. Technical Manual No. 9-1300-214, with Changes 1–4. Headquarters, Department of the Army. 10. Pirospravka. Handbook of explosives, gunpowder and pyrotechnic compositions, Sixth edition, 2012. 11. Markovsky V., Prikhodchenko I. Unguided rockets of the S-8 type. M-Hobby, 2013, No.9 (148), pp.44–50.

Claims

CLAIMS 1. A warhead comprises a body (1), wherein the outer diameter of the head part is equal to a value from the range from 75 mm to 85 mm, a safety and arming mechanism (2) located in the bottom part of the body, an explosive charge (3) containing a composition not less than 70% of RDX, or HMX, or HNIW (CL-20) with a hollow cavity in the head of the charge, a waveshaper (4), a fairing (6) and a liner (5) located in the hollow cavity, wherein ^ the liner is made of a material with a density of 8 g/cm³ to 10 g/cm³, ^ the outer surface of the liner, adjoining to the explosive, and the inner surface of the liner are made in the form of rotation surfaces with a common axis, with a wide open edge, called the base, and a narrow part on the other side, called the top, ^ the opening angle α at the base of the liner is taken between the tangents to two opposite meridians of the inner surface at the base, ^ the inner diameter D of the liner base is from 60 mm to 75 mm, the safety and arming mechanism is a self-sufficient base fuze or part of a head-bottom fuze, operating in conjunction with a piezoelectric generator (10), to provide an electric circuit between them, a conductor (7) inserted into the waveshaper, a conductive cone (8), an insulating clamping ring (9), or an electric cable, or other items used in the electric circuit, characterized in that the generatrix of the inner surface of the liner is made in the form of a line without breaking points, located inside the figure formed by small arcs of two circles passing through the ends of the line segment connecting the base of the liner from the inside with the top, the beginning of the rounding of the top, the beginning of the cylindrical part or another tip at its top, having radii equal to two and a half lengths of the specified segment, the centers of which are located on opposite sides of this segment, a doubled angle between the segment and the liner axis is from 23° to 125°; at the same time, in the parallel of the outer surface at a distance l from the base along the axis of the liner, the thickness of the liner δ_l is specified, determined along the normal to the inner surface, l is from 2 mm to 8 mm, wherein δ_l is in the range from 1.2 mm to 3 mm, and δ_l does not exceed 2.6 mm if an explosive with a density of ρ < 1.7 g/cm³ is used in the charge.

2. A warhead according to claim 1, characterized in that for the opening angle α at the base of the liner that satisfies the condition: 15° ≤ α < 25°, the value of the thickness δ_l, depending on the density ρ of the explosive used, is selected in the range from 1.31 mm to 2.01 mm at 1.6 g/cm³ ≤ ρ < 1.7 g/cm³, in the range from 1.43 mm to 2.16 mm at 1.7 g/cm³ ≤ ρ < 1.8 g/cm³, in the range from 1.55 mm to 2.31 mm at 1.8 g/cm³ ≤ ρ < 1.9 g/cm³, in the range from 1.66 mm to 2.45 mm at 1.9 g/cm³ ≤ ρ ≤ 2 g/cm³.

3. A warhead according to claim 1, characterized in that for the opening angle α at the base of the liner that satisfies the condition: 25° ≤ α < 35°, the value of the thickness δ_l, depending on the density ρ of the explosive used, is selected in the range from 1.36 mm to 2.08 mm at 1.6 g/cm³ ≤ ρ < 1.7 g/cm³, in the range from 1.48 mm to 2.23 mm at 1.7 g/cm³ ≤ ρ < 1.8 g/cm³, in the range from 1.60 mm to 2.37 mm at 1.8 g/cm³ ≤ ρ < 1.9 g/cm³, in the range from 1.71 mm to 2.52 mm at 1.9 g/cm³ ≤ ρ ≤ 2 g/cm³.

4. A warhead according to claim 1, characterized in that for the opening angle α at the base of the liner that satisfies the condition: 35° ≤ α < 45°, the value of the thickness δ_l, depending on the density ρ of the explosive used, is selected in the range from 1.41 mm to 2.14 mm at 1.6 g/cm³ ≤ ρ < 1.7 g/cm³, in the range from 1.53 mm to 2.29 mm at 1.7 g/cm³ ≤ ρ < 1.8 g/cm³, in the range from 1.65 mm to 2.44 mm at 1.8 g/cm³ ≤ ρ < 1.9 g/cm³, in the range from 1.76 mm to 2.59 mm at 1.9 g/cm³ ≤ ρ ≤ 2 g/cm³.

5. A warhead according to claim 1, characterized in that for the opening angle α at the base of the liner that satisfies the condition: 45° ≤ α < 55°, the value of the thickness δ_l, depending on the density ρ of the explosive used, is selected in the range from 1.46 mm to 2.21 mm at 1.6 g/cm³ ≤ ρ < 1.7 g/cm³, in the range from 1.58 mm to 2.36 mm at 1.7 g/cm³ ≤ ρ < 1.8 g/cm³, in the range from 1.70 mm to 2.51 mm at 1.8 g/cm³ ≤ ρ < 1.9 g/cm³, in the range from 1.81 mm to 2.65 mm at 1.9 g/cm³ ≤ ρ ≤ 2 g/cm³. 6. A warhead according to claim 1, characterized in that for the opening angle α at the base of the liner that satisfies the condition: 55° ≤ α < 65°, the value of the thickness δ_l, depending on the density ρ of the explosive used, is selected in the range from 1.51 mm to 2.28 mm at 1.6 g/cm³ ≤ ρ < 1.7 g/cm³, in the range from 1.63 mm to 2.42 mm at 1.7 g/cm³ ≤ ρ < 1.8 g/cm³, in the range from 1.75 mm to 2.57 mm at 1.8 g/cm³ ≤ ρ < 1.9 g/cm³, in the range from 1.86 mm to 2.72 mm at 1.9 g/cm³ ≤ ρ ≤ 2 g/cm³. 7. A warhead according to claim 1, characterized in that for the opening angle α at the base of the liner that satisfies the condition: 65° ≤ α < 75°, the value of the thickness δ_l, depending on the density ρ of the explosive used, is selected in the range from 1.56 mm to 2.34 mm at 1.6 g/cm³ ≤ ρ < 1.7 g/cm³, in the range from 1.68 mm to 2.49 mm at 1.7 g/cm³ ≤ ρ < 1.8 g/cm³, in the range from 1.80 mm to 2.64 mm at 1.8 g/cm³ ≤ ρ < 1.9 g/cm³, in the range from 1.91 mm to 2.79 mm at 1.9 g/cm³ ≤ ρ ≤ 2 g/cm³. 8. A warhead according to claim 1, characterized in that for the opening angle α at the base of the liner that satisfies the condition: 75° ≤ α < 85°, the value of the thickness δ_l, depending on the density ρ of the explosive used, is selected in the range from 1.61 mm to 2.40 mm at 1.6 g/cm³ ≤ ρ < 1.7 g/cm³, in the range from 1.72 mm to 2.55 mm at 1.7 g/cm³ ≤ ρ < 1.8 g/cm³, in the range from 1.84 mm to 2.70 mm at 1.8 g/cm³ ≤ ρ < 1.9 g/cm³, in the range from 1.96 mm to 2.85 mm at 1.9 g/cm³ ≤ ρ ≤ 2 g/cm³. 9. A warhead according to claim 1, characterized in that for the opening angle α at the base of the liner that satisfies the condition: 85° ≤ α ≤ 125°, the value of the thickness δ_l, depending on the density ρ of the explosive used, is selected in the range from 1.65 mm to 2.47 mm at 1.

6 g/cm³ ≤ ρ < 1.7 g/cm³, in the range from 1.77 mm to 2.62 mm at 1.

7 g/cm³ ≤ ρ < 1.8 g/cm³, in the range from 1.89 mm to 2.77 mm at 1.

8 g/cm³ ≤ ρ < 1.9 g/cm³, in the range from 2.01 mm to 2.92 mm at 1.

9 g/cm³ ≤ ρ ≤ 2 g/cm³.

10. A warhead according to claim 3, characterized in that the liner is made in the form of a side surface of a right circular cone, the opening angle α, the same for the entire liner, satisfies the condition: 25° ≤ α < 35°.

11. A warhead according to claim 10, characterized in that the difference of the opening angles of the outer and inner surfaces (β - α), depending on the density ρ of the explosive used, is selected in the range from 0°45' to 1°15' at 1.6 g/cm³ ≤ ρ < 1.7 g/cm³, in the range from 0°50' to 1°20' at 1.7 g/cm³ ≤ ρ < 1.8 g/cm³, in the range from 0°55' to 1°25' at 1.8 g/cm³ ≤ ρ < 1.9 g/cm³, in the range from 1° to 1°30' at 1.9 g/cm³ ≤ ρ ≤ 2 g/cm³.

12. A warhead according to claim 4, characterized in that the liner is made in the form of a side surface of a right circular cone, the opening angle α, the same for the entire liner, satisfies the condition: 35° ≤ α < 45°.

13. A warhead according to claim 12, characterized in that the difference of the opening angles of the outer and inner surfaces (β - α), depending on the density ρ of the explosive used, is selected in the range from 1° to 1°30' at 1.6 g/cm³ ≤ ρ < 1.7 g/cm³, in the range from 1°5' to 1°35' at 1.7 g/cm³ ≤ ρ < 1.8 g/cm³, in the range from 1°10' to 1°40' at 1.8 g/cm³ ≤ ρ < 1.9 g/cm³, in the range from 1°15' to 1°45' at 1.9 g/cm³ ≤ ρ ≤ 2 g/cm³.

14. A warhead according to claim 5, characterized in that the liner is made in the form of a side surface of a right circular cone, the opening angle α, the same for the entire liner, satisfies the condition: 45° ≤ α < 55°.

15. A warhead according to claim 14, characterized in that the difference of the opening angles of the outer and inner surfaces (β - α), depending on the density ρ of the explosive used, is selected in the range from 1°15' to 1°45' at 1.6 g/cm³ ≤ ρ < 1.7 g/cm³, in the range from 1°20' to 1°50' at 1.7 g/cm³ ≤ ρ < 1.8 g/cm³, in the range from 1°25' to 1°55' at 1.8 g/cm³ ≤ ρ < 1.9 g/cm³, in the range from 1°30' to 2° at 1.9 g/cm³ ≤ ρ ≤ 2 g/cm³.

16. A warhead according to claim 6, characterized in that the liner is made in the form of a side surface of a right circular cone, the opening angle α, the same for the entire liner, satisfies the condition: 55° ≤ α < 65°.

17. A warhead according to claim 16, characterized in that the difference of the opening angles of the outer and inner surfaces (β - α), depending on the density ρ of the explosive used, is selected in the range from 1°30' to 2° at 1.6 g/cm³ ≤ ρ < 1.7 g/cm³, in the range from 1°35' to 2°5' at 1.7 g/cm³ ≤ ρ < 1.8 g/cm³, in the range from 1°40' to 2°10' at 1.8 g/cm³ ≤ ρ < 1.9 g/cm³, in the range from 1°45' to 2°15' at 1.9 g/cm³ ≤ ρ ≤ 2 g/cm³.

18. A warhead according to claim 7, characterized in that the liner is made in the form of a side surface of a right circular cone, the opening angle α, the same for the entire liner, satisfies the condition: 65° ≤ α < 75°.

19. A warhead according to claim 18, characterized in that the difference of the opening angles of the outer and inner surfaces (β - α), depending on the density ρ of the explosive used, is selected in the range from 1°45' to 2°15' at 1.6 g/cm³ ≤ ρ < 1.7 g/cm³, in the range from 1°50' to 2°20' at 1.7 g/cm³ ≤ ρ < 1.8 g/cm³, in the range from 1°55' to 2°25' at 1.8 g/cm³ ≤ ρ < 1.9 g/cm³, in the range from 2° to 2°30' at 1.9 g/cm³ ≤ ρ ≤ 2 g/cm³.

20. A warhead according to any of preceding claims, characterized in that the liner is made of metals, including bimetals, or metal alloys, including powder and pseudo-alloys, or metal polymers, preferably having anti-corrosion coating.

21. A warhead according to any of preceding claims, characterized in that the liner is made of copper with a total mass fraction of impurities of less than 0.1%.

22. A warhead according to any of preceding claims, characterized in that the liner thickness along any parallel of the inner or outer surface is determined along the normal to the inner surface and has a tolerance of less than ±0.05 mm.

23. A warhead according to any of preceding claims, characterized in that the liner additionally comprises elements for installation and/or initiation.

24. A warhead according to any of preceding claims, characterized in that the warhead additionally comprises a fragmentation part.