RU2593851C1 - Projectile separation compartment - Google Patents

Abstract

FIELD: rocketry.

SUBSTANCE: invention relates to rocketry, in particular, to projectile separation compartment. It comprises a shell with a bottom, support ring, piston, power supply with initiating device and forcing assembly, fastening separated elements. Compartment energy sources are made as combination of an augmenter charge and one or more accelerating pressure batteries. Batteries are symmetrically fixed in the piston and equipped with initiating devices. Augmenter charge is fixed in the support ring by means of diaphragm and has a toroidal shape, and is arranged around the safety-actuating mechanism. Safety-actuating mechanism is equipped with a radial initiating device. Device is aligned with local thinning on the inner surface of the toroid. Thinning is made by means of axial pins on the support surface of the charge body and mating head of fixing screw installed on the diaphragm surface adjacent to the body. Powder pressure batteries are symmetrically fixed in the piston and equipped with initiating devices. Said devices are made in the form of igniters and breaking membranes, fixed in the zone of batteries nozzle units. Membranes have regulated power and thermal conditions of operation in the separation process. This provides opening of gas-dynamic connections of batteries combustion chambers with the projectile separation cavity into a required moment of time.

EFFECT: higher reliability of projectile separation compartment design, decreased passive weight, increased speed of separation at reduced power and heat effects on separated elements.

1 cl, 1 dwg

Description

The invention relates to the field of rocketry and can be used in the development of multiple munitions of rocket and barrel artillery.

The solution of this problem is associated with the need to develop rational design options for the fixation and tamper units, ensuring the rigidity of the projectile during high-speed movement along the trajectory and the reliability of separation of fragments of a separated missile projectile (PC) with minimal power and thermal loads on the shared structural elements. This is especially important for multiple shells that are equipped with intelligent elements or unmanned aerial vehicles (UAVs) equipped with vulnerable electronic equipment.

According to the patent of Russia RU (11) No. 2230288 dated November 21, 2002 (Russian Federation. "Patents of the Russian Federation for Inventions", No. 16 dated June 10, 2004), the design of a fissionable projectile is known. The projectile contains a rocket engine with a body, a bottom and a charge of solid fuel and a detachable warhead, comprising a body with striking elements, a parachute compartment in the form of a casing with a bottom, a powder charge with a safety-executive mechanism (PIM), separation, opening and fixation.

The separation unit is located between the casing of the software and the bottom of the rocket part and is equipped with a cylindrical guide, in which the fixing elements of the segment shape are placed, interacting with the inner conical surface of the hull.

The operation of the indicated design of the projectile with the parachute stabilization system has some similarities with the work of the design of the multiple-projectile projectile proposed by the authors, which suggests that there is a piston-type separation system in the known structural solution that has an energy source with initiation means. However, the lack of constructive design of these units in the application materials does not allow for a concrete comparison of their positive practical qualities.

Thus, the objective of the considered structural solution was the development of a separable rocket projectile, which ensures separation of the head from the rocket engine, the launch of the parachute system and the descent of the head in the target area at low power loads and the passive mass of ammunition.

Common features with the proposed design of the PC is the presence of a separation compartment with an energy source (compartment charge) and an initiating device in the form of a safety-executive mechanism.

According to international application No. 88/05523 of 07/28/08, cl. F42B 13/38 (ISM No. 3, issue 105, 1989) there is a known design of a separable projectile containing a head with a parachute compartment, a separation unit with a separation charge and forcing elements in the form of cut radial bolts.

The design of the multiple projectile allows the separation of the warhead from the carrier and the launch of the parachute. However, this design does not ensure the operation of the structure in conditions of unstabilized high-speed movement of the head part, characterized by the formation of large forces of "frontal" drag on the trajectory.

Thus, the objective of this technical solution was to ensure the separation of the head part from the carrier by means of a separation unit with forcing elements in the form of cut-off radial bolts, as well as putting the parachute into operation in conditions of stable movement of the head part.

Common features of the known technical solution with the design of the separation compartment proposed by the authors is the presence of a separation unit with forcing elements and a charge of separation, which is a source of energy during separation.

The closest in technical essence and the achieved result is a multifunctional rocket separation compartment, known according to the Russian patent RU (11) No. 2459176 (13) C1 dated April 21, 2011 (published in Bul. No. 23 08/08/2012)

The multifunctional rocket separation compartment contains a housing, docking units for the head and engine, locking mechanisms, a stabilization system for the detachable warhead, as well as separation, opening, initiating and actuating units for the warhead, which include powder charges, pistons and boost elements.

The objective of the described invention is to develop the design of a multifunctional compartment for separating missiles, which ensures the fixation and opening of the stabilization system for the warhead, the separation and stabilization of the warhead in flight, the initiation and activation of the actuators of the compartment and warhead during operation.

The practical implementation of the totality of the design differences presented above in the developed ammunition makes it possible to create a unified multifunctional design of the separation compartment, which ensures the reliable functioning of rockets for various purposes on the active and passive sections of the trajectory. However, due to the multifunctionality, complexity and high cost of the unified design, in this case, the use of this invention seems to be inappropriate.

Common features of the described technical solution adopted by the authors for the prototype with the proposed design of the shell separation compartment is the presence of a separation unit with a powder charge, piston and forcing elements.

In contrast to the prototype in the proposed design solution, the compartment energy source is made in the form of a combination of afterburner charge and one or several accelerating powder pressure accumulators (PAD), symmetrically fixed in the piston and equipped with initiating devices.

The afterburner charge is fixed in the support ring by means of a diaphragm and is made in the form of a toroidal shape placed around the safety-actuating mechanism, equipped with a radial initiating device oriented with local thinning on the inner surface of the torus, for example, by performing axial bubbling on the supporting surface of the charge housing and the presence of mating head of the fixing screw mounted on the diaphragm surface adjacent to the housing.

Gunpowder pressure accumulators are symmetrically fixed in the piston and equipped with initiating devices made in the form of igniters and bursting membranes fixed in the area of the nozzle blocks of the batteries and having regulated power and thermal conditions of operation during the separation process, which ensure opening of the gas-dynamic connections of the battery combustion chambers with the shell separation cavity at the right time.

These distinctive features, to which the requested amount of legal protection applies, are substantial and sufficient to achieve a new technical result.

The objective of the invention is to develop a simple, compact and reliable design of the compartment for separation of shells, which provides the possibility of a significant increase in the speed of separation while reducing power and thermal effects on the shared structural elements and, first of all, on the guided air reconnaissance vehicle, located in the shell of the head of the reactive reconnaissance shell.

The specified technical result is achieved due to the fact that in the known design of the separation compartment of a rocket containing a shell with a bottom, a support ring, a piston, an energy source with an initiating device and a forcing unit fastening the shared structural elements, a new set of structural units and elements has been introduced, changed their mutual arrangement, as well as kinematic and gas-dynamic relationships.

In particular, the implementation of the energy source in the form of a combination of afterburner charge and one or more booster pressure accumulators (PAD), equipped with initiating devices, allows, due to the selection of rational parameters for charging the afterburner charge and energy characteristics of the PAD, to ensure:

low level of maximum pressure in the separation cavity, slightly higher than the fracture pressure of the explosive bolts of the forcing unit;

the ability to easily enough solve the problem of obtaining the required speed of separable structural elements due to the choice of the number and duration of operation of the PAA in the separation process;

operability of the design due to the competent selection of the parameters of the initiating devices.

In this case, the symmetrical fastening in the piston of the booster pressure accumulators eliminates the eccentricity of the mass of the ammunition in the process of movement along the trajectory and, thus, ensures a stable movement of the ammunition. At the same time, in this case, it is possible to use the traction of PADs as an additional accelerating force that increases the acceleration speed of one of the separated objects.

Fixing the afterburner charge in the support ring by means of a diaphragm and making it in the form of a toroidal shape placed around a safety-actuating mechanism equipped with a radial initiating device oriented with local thinning on the inner surface of the torus provides a simple and reliable actuation of the charge when an ignition pulse is applied, for example , from the control unit.

The supply of pressure accumulators with initiating devices made in the form of igniters and bursting membranes, mounted on the nozzle blocks of the batteries and having regulated power and thermal conditions of operation during the separation process, ensures reliable opening of the nozzle blocks and the gas-dynamic connection of the combustion chambers of the batteries with the shell separation cavity at the required time .

The design features listed above make it possible to solve the problem of developing a simple, compact and reliable design for the projectile separation compartment, which makes it possible to reduce the power and thermal effects on the shared structural elements and, first of all, on the UAV, which has vulnerable electronic components in its composition. This, ultimately, allows to reduce the passive weight and increase the reliability of the developed design in flight conditions.

The essence of the invention is illustrated by drawings, where in FIG. 1 shows a general view of the separation compartment and a view of the separation compartment from the bottom.

The proposed design of the separation section of the rocket shell contains a shell 1 with a bottom 11, a support ring 9, a piston 2 and a forcing unit 5 fastening shared structural elements (a piston with a payload and a support ring with a shell and a bottom).

The energy source is made in the form of a combination of afterburner charge 16 and one or more accelerating pressure accumulators 3, symmetrically mounted in the piston and equipped with initiating devices 6, 7.

The afterburner charge 16 is fixed in the support ring 9 by means of the diaphragm 12 and is made in the form of a toroidal shape placed around the safety-actuating mechanism 18, equipped with a radial initiating device 17, oriented with local thinning 15 on the inner surface of the torus, for example, by performing axial puffing 14 on the supporting surface of the charge housing and the presence of the response head of the fixing screw 13 mounted on the diaphragm surface adjacent to the housing.

Gunpowder pressure accumulators 3 are symmetrically fixed in the piston 2 and equipped with initiating devices made in the form of igniters 6 and bursting membranes 7 fixed in the areas of the nozzle blocks 8 of the accumulators and having regulated power and thermal conditions of operation during the separation, which ensure opening of the gas-dynamic connections of the combustion chambers accumulators A with a cavity for separating the projectile B at the required time.

The functioning of the shell separation compartment begins with the operation of the receiving device 19, activating the PIM 18 and the operation of the powder firecracker 17. The combustion products of the firecrackers are sent to thinning in the housing 15, destroy it and provide reliable ignition of the afterburning powder charge 16, which is the energy source for the PC separation process.

Charge combustion products fill the free cavities of the main working volume B and fill the adjacent working volume B through the supply channels in the support ring 10 and the diaphragm 12. At a pressure corresponding to the destruction force of the forcing unit 5, the process of separation of the projectile begins under pressure on the piston 2.

Almost simultaneously, due to the regulation of the operating conditions of the membranes 7 fixed in the region of the nozzle blocks of pressure accumulators 8, they are destroyed and a gas-dynamic connection of the cavities of the PAD (A) combustion chambers with the cavity of the projectile B separation is formed. As a result, due to the arrival of dense high-temperature combustion products afterburner charge in the chamber PAD igniters 6 are activated and enable the use of powder charges of 4 batteries. Combustion products formed in the free zones of PAD through nozzle channels enter the separation zones B and C. A powerful pressure rise and effective acceleration of the piston with a payload begin.

The PC separation process is accompanied by a sharp increase in the piston volume of the separation zone, however, due to the accumulation of pressure in the cavity B and the powerful influx of energy from the PAD chambers along the entire length of the guide shell 1, the required values of the speeds of the separated elements are achieved. The magnitude of the maximum pressure in the separation zone, and hence the overload, is determined by the choice of mass of the afterburner charge, and the value of the relative speed of the objects to be separated is determined by the choice of mass and body of combustion of the PAD charges.

When the piston 2 exits from the shell 1, the pressure in the working zones is released and the process of separation of the components of the projectile is completed, including on the one hand the piston 2 with the payload of the head, and on the other hand, the ring 9 with the shell 1, the bottom 11 and passive rocket elements parts.

Thus, the practical implementation of the totality of the design differences presented above in the developed ammunition allows us to solve the problem of developing a simple, compact and reliable design of the shell separation compartment, which makes it possible to reduce the power and thermal effects on the shared structural elements and, first of all, on the UAV, which has vulnerable electronic components in its composition. This, ultimately, allows to reduce the passive weight and increase the stability of the developed design in flight conditions. At the same time, there is a wide opportunity, due to the choice of the number and mass of PADs, to sharply increase the relative velocity of the separated projectile elements.

The invention can be used in the development of separable missiles with detachable warheads and, primarily, when creating new and modernizing existing designs of multiple launch rocket systems, which reduces the time and cost of working out the developed samples.

The indicated positive effect is confirmed by the results of numerous bench tests of prototypes of separation compartments, made in accordance with the alleged invention.

Claims (1)

The shell separation compartment comprising a shell with a bottom, a support ring, a piston, a boost assembly and energy sources with initiating devices, characterized in that the energy sources in it are made in the form of a combination of afterburning powder charge and one or more accelerating powder pressure accumulators equipped with initiating devices wherein the afterburner charge is fixed in the support ring by means of a diaphragm and is made in the form of a toroidal product placed around a safety-executive mechanism equipped with a radial initiating device, oriented with local thinning on the inner surface of the torus, for example, by performing axial marking on the supporting surface of the charge housing and the presence of a response head of the fixing screw mounted on the diaphragm surface adjacent to the housing, and the powder pressure accumulators are symmetrically fixed in the piston and equipped with initiating devices made in the form of igniters and bursting membranes, fixed in the area of the nozzle blocks accumulators and having regulated power and thermal conditions of operation during the separation process, ensuring the opening of the gas-dynamic connections of the combustion chambers of the batteries with the shell separation cavity at the required time.

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