RU2686546C1 - Armor piercing active-missile - Google Patents

Abstract

FIELD: weapons and ammunition.SUBSTANCE: invention relates to active-jet projectiles with armor-piercing feathered subcaliber core. Armor-plucking sweep projectile contains penetrating sub-caliber core and driving device. Penetrating core is combined with solid fuel straight-flow air-jet engine, which includes housing, input device, fuel charge, combustion chamber and nozzle. Penetrating core head part is used as the central body. This body provides supersonic flow braking with pressure and temperature increase, which provide initiation of combustion of fuel charges. These fuel charges are installed so that they form ring on internal walls of combustion chamber.EFFECT: high armor penetration at long distances.6 cl, 2 dwg

Description

Armor-piercing active-missile refers to ammunition and can be used to increase the armor penetration of the projectile at medium and long distances.

A well-known design of a kinetic ammunition, in which the rocket engine is located around the armor-piercing core of high elongation - MRM-KE [42nd Annual Armament Systems: Charlotte, North Carolina, 23-26 April 2007].

The considered design contains the following basic elements: drop-down stabilizer blades, composite body, solid propellant jet engine (RDTT), penetrating core, correction engines, power battery, homing head.

The advantages of the MRM-KE design: the ability to correct the trajectory and homing, a large kinetic energy in comparison with conventional BOPS, the ability to turn on the engine in the optimal part of the trajectory. All this, theoretically, allows the use of this ammunition at long ranges.

Disadvantages of the MRM-KE design in comparison with the classic BOPS:

- Difficulty and high cost. In the first place, due to the presence of a homing system.

- Large weight and size of the structure. The use of rocket engines implies the need for an appropriate amount of oxidizer in the fuel, plus a radar homing, battery, and folding tail. The mass of the MRM-KE is twice the mass of conventional projectiles, which reduces the initial velocity and, consequently, the effectiveness of the application.

- Rapid loss of speed after fuel production. The armor-piercing core is not separated from the rest of the design, so after producing fuel it will lose kinetic energy much faster than classic BOPS, due to significant frontal air resistance.

Known designs ARS with rocket-ramjet engine solid fuel (RPDT) front location [Rocket-ramjet engines on solid and pasty fuels. Fundamentals of design and experimental development. - M .: FIZMATLIT, 2010. - 320 p. - with. 31]. The RPDT of the projectile cited in the example, as well as the engine of the construction proposed in this application, is located at the front and has a central body, which is the head part of the projectile. The engine of this projectile has an input device, a combustion chamber, a nozzle, nozzle openings of the gas generator, and a charge of solid fuel for end combustion.

The disadvantage of this and similar solutions is the use of end-combustion charges with channels leading to the combustion chamber, which is more properly called an afterburner, since already partially oxidized particles (primary combustion products) enter the combustion chamber. This design also implies the presence of a considerable amount of oxidizing agent. In addition, the displacement of the center of mass with the burning of such a charge may adversely affect the accuracy.

The design of the two-stage rocket R-3 I.A. Merkulov, with a ramjet solid-fuel engine (RDC engine) as the second stage [Rocket-ramjet engines on solid and pasty fuels. Fundamentals of design and experimental development. - M .: FIZMATLIT, 2010. - 320 p. - with. 15-16]. The main elements of the rocket: the input device scramjet, the charge of fuel scramjet, the charge of the fuel solid propellant rocket motor, aerodynamic brake, aerodynamic stabilizer, nozzle, reset plug This design, as well as the proposed technical solution, involves the use of ring-shaped charges of solid fuel, which implies a large area of interaction of the surface of the charges with atmospheric air. The disadvantage of the example device, is the design of the input device with an expanding cone, characteristic of low-performance subsonic GTRD.

Known armor piercing subcaliber shells (BOPS) with leading devices [see. RF patent №2347177]. Such projectiles contain a ballistic tip, a sector master device, a feather stabilizer, and a multi-core core. To obtain high rates of armor penetration of such weapons, both a large mass of an armor-piercing feathered sub-caliber projectile (BOPS) and a high initial velocity with a small diameter and large elongation are needed. Improving performance in both mass and speed is in conflict with each other. Modern sub-caliber feathered shells develop a speed of about 1500-1800 m / s. The speed drop on the flight path is approximately 50 m / s for every 1000 meters. While the best armor penetration can be obtained at shock speeds of 2000-2500 m / s. Increasing the impact speed to hypersonic 3000 m / s and more does not lead to a further increase in armor penetration, since in this case the bulk of the projectile energy will be spent on increasing the diameter of the crater. A further increase in the mass, length and speed of the BOPS is faced with the need to move to large caliber guns and new automatic loaders, which leads to a decrease in ammunition and increases the requirements for the platform on which the gun is placed.

The use of active-rocket projectiles (APC), which allow to accelerate and maintain a high velocity of a heavy projectile after the projectile leaves the barrel, is a well-known method. However, in the case of BOPS, active-missiles were not found to be of practical use.

An object of the invention is to increase the achievable without increasing the caliber and length of the projectile - the mass, speed and range of flight of an armor-piercing feathered subcaliber arrow-shaped core, in order to increase armor penetration at medium and long distances. In contrast to high-explosive ARS on ramjet, for which the main indicator is long-range, the task of arcs with an armor-piercing core is to achieve the maximum possible speed for a classic ramjet in the shortest period of time, followed by the separation of the core and engine.

This technical problem in the framework of the present invention is solved by the fact that the body of the ramjet is located inside the master device (WU) and, in one of the paragraphs, they are combined into one device. The role of the central body, providing external deceleration of the supersonic flow, is played by a ballistic tip of a characteristic conical shape, providing several shock waves. Considering the fact that the initial speed of the BOPS, as a rule, is higher than the PZM and air consumption of the ramjet engine of the proposed design will be more significant than in the high-explosive ARS, the initial speed of which, as a rule, is not more than 2.5 M, and also taking into account the task of acceleration up to 2000 m / s (almost 6M at the ground), i.e. up to the maximum for modern ramjet speed, it was decided to abandon common designs with a gas generator having channels into the combustion / afterburning chamber and using cylindrical charges of solid butt burning fuel, in favor of the charges forming a ring with a longitudinal central channel. Such charges will ensure a significant contact of the fuel surface with the incoming air, which ensures its faster combustion and allows reducing the amount of oxidizer in the composition. Also, the proposed charges lead to a smaller displacement of the center of mass as it burns out. In addition, as acceleration and, consequently, increase in air flow, the burning area will constantly increase until the fuel charges burn out, continuing to accelerate. Additionally, it is possible to place smaller fuel charges with a ring around the core, leaving a gap relative to the ring of charges located on the inner walls of the ramjet.

When a projectile is fired, a load arises that is capable of deforming the charges of highly metallized solid fuel, to avoid such an effect, the charges are closed by perforated plates of high-strength and heat-resistant materials.

Due to the placement of the rocket engine inside a conventional sector breakaway by the air flow of the ACU or the combination of the ACU with the RAMER in a single device, it is possible to save the volumes of propellant charge to disperse the projectile. Combining WU with ramjet in a single device implies the presence of leading belts on the ramjet housing, ensuring reliable obturation of the bore and the obligatory presence of a detachable tray that protects the nozzle from the entry of powder gases when fired.

After the production of fuel, the task of separating the ramjet and the core for a significant reduction in drag. The task can be solved in different ways, for example: the fasteners are located in two sections - at the ballistic tip and closer to the center of the core, with a thickening on the core body. In this case, the role of thickening on the body of the core can simply play a narrowing of its diameter. The distance between the anchors at the ballistic tip should be greater than the diameter of the thickening on the core body. Mounts on all sections must be made with gaps, providing the possibility of passage of the tail of the tail core. The plumage itself is made of small span, capable of passing through an annular air intake. The tail materials mean high heat resistance and heat resistance, as they are subject to the influence of a jet stream. For a combination of durable fastening during transportation, filing and firing with a slight separation in flight, you can use a thin layer (solder) of the fusible metal between the mount and the surface of the core.

The proposed construction is illustrated graphically. FIG. 1 is a view of the invention combining claims 1-5. FIG. 2. shows the kind of invention according to item 6. The numerical designations of the common structural elements in the figures are the same. The elements of the construction of FIG. 1 are designated as follows: sector master device 1, body of a ramjet 2, fuel charges 3, fastening the core to ramjet 4, combustion chamber 5, nozzle 6, solder 7, section for reducing the diameter of the core 8, fastening a ballistic tip to ramjet 9, armor-piercing core 10 , ballistic tip 11, tail 12, perforated protective plate 15.

The elements of the construction of FIG. 2 are labeled as follows: RAMJET housing 2, fuel charges 3, fastening the core to the RAMSD 4, combustion chamber 5, nozzle 6, solder 7, section for reducing the diameter of the core 8, attaching the ballistic tip to the RAMJTT 9, armor-piercing core 10, ballistic tip II, tail 12, leading belts 13, sector pan 14, perforated protective plate 15.

The operation of the structure is carried out as follows: after departure from the bore of the projectile at supersonic speed, the driving device 1 or pallet 14 is separated by an incoming air flow. To implement this separation, these constructions are sector-wise, that is, divided into elements. In the embodiment of FIG. 2, with a pallet 14, on the body of the ramjet 2 there are located leading belts 13 for obturation of the powder gases when firing and centering the projectile in the bore. Ballistic tip 11, plays the role of the central body in the ramjet. The ballistic tip 11, due to its special conical shape in the front part, provides external compression and deceleration of air with several shock waves. Due to the conical rear part, internal braking is provided, since housing ramjet 2 and the conical back of the ballistic tip 11 form a diffuser. Due to this, the supersonic air flow is decelerated to subsonic speed, while pressure and temperature increase, which initiates the burning of fuel charges 3. Fuel charges 3 of highly metallised fuel with a small amount of oxidizer are protected from deformation and destruction when fired by perforated protective plates 15 and are placed in a ring on the inner walls of the housing TEVRDT 2. FIG. 1 shows a variant with additional fuel charges located ring around the armor-piercing core 10. In the combustion chamber 5, the main process of fuel oxidation occurs, then, thanks to the Laval nozzle 6, the working fluid accelerates to a supersonic speed exceeding the speed of oncoming flow, creating cravings. Meanwhile, high temperatures melt the solder 7, removing the rigid attachment of the core to the ramjet 4 and allowing the core 10 together with the ballistic tip 11 to exit from the ramjet 2. The output occurs after the generation of fuel charges 3, due to the difference in aerodynamic resistance between the ballistic tip 11 and bodywork HRTD 2. To be able to exit the core, attaching the ballistic tip to the RAMJET 9 and attaching the core to the RAMJET 4, at the junction points with the core 10 and the ballistic tip 11, respectively GOVERNMENTAL are formed with discontinuities for the passage of the tail 12. The tail unit 12 is rotated relative to anchorages 4 and 9 to avoid contact with them in the separation.

According to the author, the proposed design corresponds to the task and is quite simple and technological. And, despite the lower initial speed, it will allow increasing the armor penetration rate of BOPS at medium and long distances.

Claims (6)

1. Armor-piercing swept projectile containing a penetrating sub-caliber core and a master device, characterized in that the penetrating core is combined with a solid-fuel ramjet engine, comprising a housing, an input device, a fuel charge, a combustion chamber and a nozzle, while the head part of the penetrating core is used as a central body that provides supersonic flow deceleration with increasing pressure and temperature to initiate the combustion of fuel charges ring on the inner walls of the combustion chamber. 2. The projectile of claim. 1, characterized in that the solid propellant direct-flow jet-propulsion engine does not have a strong connection with the penetrating core and is provided with the possibility of separation after the fuel has been produced, while the engine is fixed to the core behind the sections of the core narrowing and made discontinuously core plumage during separation. 3. The projectile of claim. 1 or 2, characterized in that the ballistic tip of the head part of the penetrating core is adopted as the central body. 4. The projectile in one of the paragraphs. 1-3, characterized in that it has an additional fuel charge adjacent to the subcaliber core, with the gap formed between the surfaces of the fuel charges. 5. The projectile in one of the paragraphs. 1-4, characterized in that the fuel charges are closed by plates having openings for the exit of fuel particles. 6. The projectile in one of the paragraphs. 1-5, characterized in that the maximum diameter of the body of a direct-flow solid-fuel jet engine due to the leading belts playing the role of the master device corresponds to the caliber of the barrel, and the design provides for a sector pallet separated by an incoming air flow, covering the nozzle from the effects of powder gases.

Images