RU2230288C1 - Separating jet projectile - Google Patents

Separating jet projectile Download PDF

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Publication number
RU2230288C1
RU2230288C1 RU2002131355/02A RU2002131355A RU2230288C1 RU 2230288 C1 RU2230288 C1 RU 2230288C1 RU 2002131355/02 A RU2002131355/02 A RU 2002131355/02A RU 2002131355 A RU2002131355 A RU 2002131355A RU 2230288 C1 RU2230288 C1 RU 2230288C1
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RU
Russia
Prior art keywords
housing
casing
parachute
parachute compartment
cylindrical guide
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RU2002131355/02A
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Russian (ru)
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RU2002131355A (en
Inventor
Н.А. Макаровец (RU)
Н.А. Макаровец
Г.А. Денежкин (RU)
Г.А. Денежкин
Г.В. Калюжный (RU)
Г.В. Калюжный
В.И. Козлов (RU)
В.И. Козлов
В.И. Бондаренко (RU)
В.И. Бондаренко
В.В. Семилет (RU)
В.В. Семилет
А.Е. Плотников (RU)
А.Е. Плотников
Г.П. Молчанов (RU)
Г.П. Молчанов
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Федеральное Государственное унитарное предприятие "Государственное научно-производственное предприятие "Сплав"
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Priority to RU2002131355/02A priority Critical patent/RU2230288C1/en
Publication of RU2002131355A publication Critical patent/RU2002131355A/en
Application granted granted Critical
Publication of RU2230288C1 publication Critical patent/RU2230288C1/en

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Abstract

FIELD: rocketry, applicable in development of jet projectiles with separating nose cones. SUBSTANCE: the projectile has a rocket engine with a body, bottom and a solid-propellant charge, and a separating nose cone comprising a blasting device, body with destructive components, parachute compartment in the form of a housing with a bottom, powder charge with a safety-actuating mechanism, separation opening and fixation points. The separation point is positioned between the housing of the parachute compartment and the bottom of the engine body, it is provided with a cylindrical guide accommodating segment-shaped fixing members, whose inner surface corresponds to the inner surface of the guide, and the outer surface is engageable with the inner tapered surface of the nose cone body, positioned in the cylindrical guide rigidly coupled to the housing of the parachute compartment is a movable thrust ring provided with a flat flexible ring with a sealing member tightened to the outer surface of the housing by means of a plate stop. The parachute compartment opening point is positioned in the nose part of the housing, provided with a centering thickening, whose outside diameter exceeds the housing diameter, and blocks so positioned that their outer surface rests on the inner surface of the nose cone body, and the inner surface is persistently engageable with the mating tapered surface in the bottom of the parachute compartment. The fixation point is provided with studs tightening the housing of the parachute compartment to the nose cone body by means of a carrier ring, cylindrical guide and the segment-shaped fixing members. EFFECT: reduced effect of force loads acting on the separated members of the structure, provided use of destructive components that are sensitive to the effect of impact and vibratory loads. 5 dwg

Description

One of the main directions of increasing the effectiveness of the combat use of ammunition of rocket and barrel artillery is the development of ammunition that ensures separation or opening of warheads (warheads) at a given point on the trajectory. In this case, the option of separating the warhead from the missile (RF) is implemented, as a rule, for high-explosive and high-explosive fragmentation and requires the development of a parachute stabilization system that provides braking and the approach of the warhead to the earth's surface at an angle close to 90 °.
The solution of this problem is associated with the need to develop rational design options for the fixation, separation and opening units, ensuring the rigidity of the projectile when moving along the trajectory and the reliability of separation and opening of fragments of a separated missile (RRS).
According to the application of the Federal Republic of Germany (DE) No. 4002355 of September 13, 1990 (RF ISM, issue 81, MKI F42B, No. 7-9, 1991), the head part with a parachute is known. A warhead is designed to be dropped from a projectile above the target area. It has a parachute to reduce speed over the ground. The head part is characterized in that the parachute has means for rotating it at the desired speed. There is a sensitive element to search for the target area. The head part is characterized in that the parachute has means for creating rotation. They drive the parachute in rotation in the opposite direction to the rotation of the warhead.
From the above it follows that in the known head part with a parachute structural components and elements are not described that provide initial fixation, and then separation or opening of shared fragments. Thus, the objective of the known technical solution was the creation of parachute rotation means that compensate for the rotation of the warhead and thereby ensure a stable parachute shape (without twisting the lines) and braking force during the descent of the warhead in the target area.
A common sign with the proposed design of the RRS is the presence of a projectile carrier head with a parachute, which reduces the speed of approach to the target.
Another similar constructive solution is known from the materials of the international application No. 88/05523 of July 28, 88 (RF IMS, issue 105, MKI F 42 V, No. 3, 1989). A projectile with an open parachute has two adjacent to one another part, in one of which a parachute is folded. For a smooth and reliable separation of these parts (with the subsequent opening of the parachute) they are connected by honey with radial bolts. Bolts are destroyed under the influence of gases, which are formed when the pyrotechnic charge is detonated and provide separation of the separated parts. Ignition of the charge is carried out using an igniter.
Said multiple projectile is characterized by the presence of a compartment unit containing a pyrotechnic charge and forcing elements made in the form of sheared radial bolts. However, the design of the RRS under consideration has some drawbacks associated with the fact that at the time of separation of the MS, serious overloads arise, the magnitude of which depends on the destruction force of the boost elements. Considering that the design parameters of the boost elements are assigned from the condition of ensuring the required stiffness of the projectile, the process of separating the warhead from the RF is accompanied by the combined action of axial overloads and high-frequency vibrations passing through the PC case at the time of the destruction (cut) of the radial bolts. The latter has a negative effect on the performance of the constituent elements and, first of all, on electronic equipment sensitive to shock low-frequency and high-frequency overloads.
Thus, the objective of this technical solution is to develop a missile design that ensures the separation of the warhead from the RF and the launch of the parachute at power loads, governed by the conditions for the destruction of the radial bolts that hold the parts to be separated.
Common features of the described projectile with the proposed design of the RRS is the presence of a rocket engine, a warhead, a separation unit and a parachute.
The closest in technical essence of the solution and the achieved result is the design of a projectile with a parachute system, known by US application No. 5386781 A dated 12.11.92 (RF ISM, issue 081, IPC F 42 V, No. 3.1996) - prototype.
The projectile contains a rocket engine, a main parachute, a deflector, a pusher, the first and second connecting elements. The rocket engine is attached to the projectile (MS). The deflector is made of fabric and installed in the head. The first connecting elements fasten the pusher to the rocket engine. The second connecting elements connect the deflector to the push rod. When a rocket engine is fired from the head, the deflector is pushed out, as a result of which radial forces act on the rocket engine, changing the trajectory of its movement.
The head part contains a detachable unit, an exhaust parachute, a main parachute and connecting elements. Parachutes are laid in a certain way inside the hull and covered with covers. A detachable unit interacts with an exhaust parachute and, when fired from a warhead, throws it outward, revealing it, and then the main parachute associated with the head part.
Functionally, the work of the considered design of the projectile with the parachute stabilization system largely coincides with the work of the design of the multiple rocket projectile proposed by the authors, which suggests the presence of fixation, detachment and opening nodes in the known constructive solution. 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 design solution, selected as the prototype, is the development of a separable missile providing separation of the warhead from the rocket engine, the launch of the parachute system and the descent of the warhead in the target area, changing the trajectory of the rocket engine after separation to prevent collision with the warhead .
A common sign with the proposed design of the RRS is the presence of a rocket engine with a separation unit (pusher) and the head part with a parachute compartment, closed bottom (cover).
In contrast to the prototype, the proposed structural solution of the RRS has a separation unit located between the casing of the parachute compartment (ON) and the bottom of the engine housing. The separation unit is equipped with a cylindrical guide, in which there are inserted locking elements of a segmented shape, the inner surface of which corresponds to the inner surface of the cylindrical guide, and the outer surface stubbornly interacts with the inner conical surface of the head housing. At the same time, in the cylindrical guide, rigidly connected with the casing of the parachute compartment, a movable thrust ring is provided, equipped with a flat elastic ring with a sealing element pressed against the outer surface of the casing by means of a plate-shaped stop.
The opening section of the parachute compartment is located in the head of the casing and is equipped with a centering thickening, the outer diameter of which exceeds the diameter of the casing, and crackers, which are placed so that their outer cylindrical surface abuts against the inner surface of the head part housing, and the inner surface stubbornly interacts with the mating conical surface in the bottom of the parachute compartment.
The fixing unit is equipped with studs, tightening by means of a support ring, a cylindrical guide and segment fixing elements, the casing of the parachute compartment with the head part.
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 the design of a separable missile, which functions reliably with minimal values of shock power loads acting on the structural elements of the projectile during the separation process.
The specified technical result is achieved due to the fact that in the design of the known RRS containing a rocket engine with a body, a bottom and a powder charge, as well as a detachable warhead having an explosive device, a body with striking elements, a parachute compartment in the form of a casing with a bottom, powder charge with a safety-executive mechanism, knots of separation, opening and fixing, a new set of structural units and elements has been introduced, their mutual position and communication have been changed. In particular, the placement of the separation unit between the casing of the parachute compartment and the bottom of the engine housing, as well as the supply of its cylindrical guide, in which there are inserted fixing elements of a segment shape, the inner surface of which corresponds to the inner surface of the cylindrical guide, and the outer surface stubbornly interacts with the inner conical surface of the housing the head part allows you to solve a number of practically important design problems, namely:
- securely fix the software casing, rigidly connected to the cylindrical guide, in the body of the head part;
- it is successful to use the segmented shape of the locking elements with conical bearing surfaces for placement in narrow annular zones between the cylindrical guide and the main body and reliable exit from the fixation zone when axial force is applied.
The placement in the cylindrical guide of the movable ring, equipped with a flat elastic ring with a sealing element, pressed against the outer surface of the casing by means of a plate-shaped stop, allows in the proposed design solution:
- to exclude the loss of segment elements from the fixation zones during the assembly and tightening of software in the head housing;
- ensure (due to the developed surface of the rings) the axial movement of the thrust ring towards the casing and the release of the fixing elements from the body of the head part at low pressures in the separation zone, an order of magnitude less than that required for the destruction of traditional forcing units (explosive bolts or annular grooves);
- to increase the reliability of the separation unit due to the presence of the sealing unit and to prevent ingress of combustion products of the charge of the separation of the movable thrust ring, preventing the thrust ring from moving to the extreme left position.
Placing the opening unit of the software in the head part of the casing and supplying it with a centering thickening, the outer diameter of which exceeds the diameter of the casing, and breadcrumbs placed so that their outer cylindrical surface abuts against the inner surface of the main body of the warhead, and the inner surface stubbornly interacts with the mating conical surface in bottom software allows you to:
- initially fix the software in the main body and exclude its radial displacements during rotation of the head during trajectory movement, and then (after the clamps go beyond the cutoff of the main body in the separation process) to ensure unhindered exit of the locking elements from the conical groove of the bottom and release the software cover;
- reset the casing and put the parachute into operation without the use of additional mechanisms, i.e. due to the aerodynamic effect of the high-speed air pressure on the annular platform of the centering thickening, the value of which depends on the difference between the diameters of the thickening and the casing and is selected from the conditions of motion of the PC at the time of separation.
The supply of the fixing unit with studs, tightening by means of a support ring, a cylindrical guide and segment fixing elements, the software housing with the head part (due to the assignment of torque) during assembly makes it possible to select all axial clearances in the power chain and provide the required structural rigidity of the RRS.
Thus, the listed design features of the RRS allow, due to the proposed version of the fixation, separation and opening units, to solve the problem and develop a projectile that functions reliably with minimal impact power loads acting on the structural elements of the projectile during separation. Reducing the level of power loading, as well as the lack of the need to use an additional mechanism (for example, a pyrotechnic type) for the forced opening of the parachute compartment, reduces the passive mass of the created sample.
The essence of the alleged invention is illustrated by drawings, where figure 1 shows a General view of the RRS, and figure 2-5 cross section of the structure.
The separable missile contains a rocket engine with a housing 1, a bottom 2 and a solid fuel charge 3 and a detachable warhead comprising an explosive device 4, a housing 5 with striking elements 6, a parachute compartment in the form of a casing 7 with a bottom 8, a powder charge 9 with a safety-executive mechanism 10, units of the compartment 11, opening 12 and fixing 13.
The separation unit is located between the casing 7 of the RF and the bottom 2 of the RF and is equipped with a cylindrical guide 14, in which the fixing elements of the segmented shape 15 are placed, the inner surface of which corresponds to the inner surface of the cylindrical guide, and the outer surface stubbornly interacts with the inner conical surface of the RF casing. At the same time, in the cylindrical guide 14, rigidly connected with the casing 7 of the software, a movable thrust ring 16 is provided, equipped with a flat elastic ring 17 with a sealing element 18, pressed against the outer surface of the casing by means of a plate-shaped stop 19.
The opening unit 12 of the software is located in the head part of the casing 7. It is equipped with a centering thickening 20, the outer diameter of which exceeds the diameter of the casing, and crackers 21, placed so that they abut against the inner surface of the main body of the chassis, with the possibility of interaction with the conical surface in the bottom of the software .
The fixing unit is equipped with studs 22, tightening by means of a support ring 23, a cylindrical guide 14 and locking elements 15, 21, the casing of the parachute compartment with the head part.
Separating missile works as follows.
After the launch of the projectile and reaching the set point of the trajectory, the safety-actuating mechanism 10 activates and transfers the initiating impulse to the charge of the compartment 9. Charge combustion products fill the working cavity between the bottom of the RF 2 and rings 16, 17. Under the action of low pressures on the developed surface of the rings, they begin to move smoothly on the inner surface of the cylindrical guide. In the process of movement due to the bending of the elastic ring 17, a constant compression of the sealing element 18 is ensured (preliminary compression is carried out by a disk stop 19) and sealing of the annular zone is required to prevent it from building up pressure that counteracts the movement of the rings.
When the rings are moved by an amount exceeding the width of the segmented locking elements 15, the latter are released and, under the action of the axial force, disengage.
At this moment, the cylindrical guide 14, rigidly connected with the casing ON 7, is released and under the influence of pressure on the casing the parachute compartment along with the head part begins to shoot from the casing 5.
In the process of shooting, the locking elements 21 are moved along the inner surface of the housing of the warhead 5 and when leaving it lose their supporting surface, disengage and release the casing 7 from the mount with the bottom 8.
In the process of separating the warhead from the rocket centering thickening 20, moving along the inner surface of the housing 5, provides centering of the detachable warhead, eliminating the appearance of vibration loads in it, as well as sealing the working volume, preventing the discharge of combustion products into the atmosphere. After the thickening leaves the section of the body of the warhead, aerodynamic forces and moments begin to act on it. As a result of aerodynamic impact, the casing of the software is pulled together from the guide section of the bottom 8, is captured by the incoming air flow and ensures the introduction of the parachute into action. The head part is stabilized and when reaching the target area is activated.
Thus, the above structural differences of the claimed RRS allow you to develop the design of a rocket, which ensures reliable operation during the separation on the trajectory with minimum values of shock power loads, contributing due to the "softness" of the separation process:
- use electronic equipment that is sensitive to shock and vibration loads;
- reduce the passive mass of structural components and elements of the projectile. The stated positive effect is confirmed by the results of the bench and flight tests of prototypes of multiple rockets equipped with detachable warheads.

Claims (1)

  1. A separable missile containing a rocket engine with a body, a bottom and a charge of solid fuel and a detachable warhead containing an explosive device, a body with striking elements, a parachute compartment in the form of a casing with a bottom, a powder charge with a safety-actuating mechanism, separation units , opening and fixing, characterized in that in it the separation unit is located between the casing of the parachute compartment and the bottom of the engine housing and is equipped with a cylindrical guide in which the fixing elec segment-shaped elements, the inner surface of which corresponds to the inner surface of the cylindrical guide, and the outer surface interacts with the inner conical surface of the body of the head part, while in the cylindrical guide rigidly connected to the casing of the parachute compartment, a movable thrust ring is provided with a flat elastic ring with a sealing element pushed to the outer surface of the casing by means of a plate-shaped stop, the opening section of the parachute compartment is located in the head th part of the casing, equipped with a centering thickening, the outer diameter of which exceeds the diameter of the casing, and breadcrumbs placed so that their outer surface abuts against the inner surface of the body of the head part, and the inner surface stubbornly interacts with the mating conical surface in the bottom of the parachute compartment, the fixing unit is equipped with studs, tightening by means of a support ring, a cylindrical guide and segment fixing elements, the casing of the parachute compartment with the body of the head part.
RU2002131355/02A 2002-11-21 2002-11-21 Separating jet projectile RU2230288C1 (en)

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Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2459176C1 (en) * 2011-04-21 2012-08-20 Федеральное Государственное унитарное предприятие "Государственное научно-производственное предприятие "Сплав" Multifunctional compartment to separate projectiles
RU2522537C1 (en) * 2013-03-13 2014-07-20 Открытое акционерное общество "Научно-производственное объединение "СПЛАВ" Detachable rocket-propelled missile
RU170324U1 (en) * 2016-04-21 2017-04-21 Акционерное общество "Новосибирский завод искусственного волокна" Separating reactive apparatus
RU205522U1 (en) * 2020-12-01 2021-07-19 Осипов Александр Федорович REACTIVE PROJECT WITH A LASER HEAD FOR DISARMING COMPLEXES OF ACTIVE PROTECTION OF TANKS

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2459176C1 (en) * 2011-04-21 2012-08-20 Федеральное Государственное унитарное предприятие "Государственное научно-производственное предприятие "Сплав" Multifunctional compartment to separate projectiles
RU2522537C1 (en) * 2013-03-13 2014-07-20 Открытое акционерное общество "Научно-производственное объединение "СПЛАВ" Detachable rocket-propelled missile
RU170324U1 (en) * 2016-04-21 2017-04-21 Акционерное общество "Новосибирский завод искусственного волокна" Separating reactive apparatus
RU205522U1 (en) * 2020-12-01 2021-07-19 Осипов Александр Федорович REACTIVE PROJECT WITH A LASER HEAD FOR DISARMING COMPLEXES OF ACTIVE PROTECTION OF TANKS

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Effective date: 20151122