RU2814088C1 - Guided missile launched from tubular guide - Google Patents

Abstract

FIELD: rocket technologies.

SUBSTANCE: guided missile launched from a tubular guide contains a control system unit located in front of the warhead, a rocket engine, a nozzle block with a contact block placed on it and drive pins interacting with the tubular guide. The projectile control system unit is also equipped with a docking unit, configured to secure the projectile in the tubular guide. The docking unit contains a groove and an electrical connector. The tubular guide is equipped with a finger to interact with the groove of the docking unit. The driving pins are configured to interact with the tubular guide and ensure rotation of the projectile around the longitudinal axis until the groove of the projectile docking unit interacts with the pin. The groove in the docking unit is designed to provide fixation of the projectile in the tubular guide, without the possibility of longitudinal movement of the projectile and excluding the possibility of its rotation in the tubular guide after loading. The electrical connector is made with an outer diameter not exceeding the calibre of the projectile. The electrical connector is fixed at a distance of 0.8-0.85 projectile lengths from the axis of the drive pins. The angle between the axis of the electrical connector and the axis of the pins is 1.1-1.3 of the angle between the axis of the pins and the axis of the contact block.

EFFECT: reliability of the functioning of a guided projectile is improved due to the reliable docking of the projectile with a tubular guide in combat conditions at different elevation angles, while maintaining the possibility of using previously developed unguided and corrected multiple launch rocket system projectiles.

2 cl, 2 dwg

Description

The proposed invention relates to the field of military equipment, namely to guided missiles of multiple launch rocket systems.

The subject of the invention is a guided missile launched from a tubular guide.

Currently, many developers have abandoned the permanent package of guides and use launchers with transport-launch containers, which simplifies the development of the projectile; for example, there is no mandatory requirement to maintain the overall weight characteristics of the projectile (see, for example, Physical basis of the design and functioning of small arms artillery and missile weapons. Part II. Physical foundations of the design and functioning of missile weapons: a textbook for universities / edited by V.V. Vetrov and Prof. V.P. Strogalev. - Tula: Tula State University Publishing House, 2007 - p. 566 - 567) accepted by the authors as an analogue.

However, the batch loading principle has disadvantages. It does not allow partial use of the contents of the packages, there is no possibility of reloading and reusing the transport and launch container, and the ability to simultaneously equip a salvo of a combat vehicle with missiles of various types is lost. At the same time, the cost of manufacturing a transport and launch container is close to the cost of a projectile, and in most cases, there is no possibility of using previously created projectiles.

Thus, the objective of this technical solution is to protect the projectile from external influences, simplify the transportation and maintenance of the projectile.

Common features with the rocket projectile proposed by the authors are the presence in the composition of the projectiles of analogues of the need to interact with the ground equipment of the combat vehicle.

The closest in technical essence to the guided missile launched from a tubular guide proposed by the authors is the “Roll-stabilized missile for launch from a tubular guide with a screw groove.” According to RF patent No. 2726103, publ. 07/09/2020, Bulletin. No. 19. It contains a control system unit located in front of the warhead, a rocket engine, a nozzle unit, with a contact block placed on it and drive pins interacting with a tubular guide.

The rocket, adopted by the authors as a prototype, functions as follows. The contact block interacts with the starting contacts of the tubular guide of the combat vehicle. From the equipment side of the combat vehicle, power is supplied to start the rocket engine, in which case the projectile is released and the latch is torn off the nozzle block. Then the drive pins move along the screw grooves of the tubular guide until the projectile exits the tubular guide.

The objective of this technical solution is to increase the reliability of the functioning of the missile during loading and preparation for launch, to reduce the mass characteristics of the projectile and, as a result, to increase the range.

At the same time, the prototype does not ensure reliable docking of the projectile with the tubular guide under combat conditions at different elevation angles while maintaining the possibility of using previously developed unguided and adjustable multiple launch rocket system projectiles.

Common features with the technical solution proposed by the authors are a control system unit located in front of the warhead, a rocket engine, a nozzle block, with a contact block placed on it and drive pins interacting with a tubular guide.

Unlike the prototype, in the proposed missile, the projectile control system unit is equipped with a docking unit, designed to ensure the fixation of the projectile in a tubular guide, the docking unit contains a groove and an electrical connector, the electrical connector is made with an outer diameter not exceeding the caliber of the projectile, and is attached to a distance of 0.8-0.85 projectile lengths from the axis of the driving pins, and the smallest angle between the axis of the electrical connector and the axis of the pins is 1.1-1.3 angles between the axis of the pins and the axis of the contact block.

In particular cases, that is, in a specific form of execution, the tubular guide is equipped with a finger to interact with the groove of the docking unit; the driving pins are designed to interact with the tubular guide and ensure rotation of the projectile around the longitudinal axis until the groove of the projectile docking unit interacts with the finger, the groove in The docking unit is designed to provide fixation in the tubular guide, without the possibility of longitudinal movement of the projectile and excluding the possibility of rotation in the tubular guide after loading; flat pair contacts are mounted on the contact block.

This allows us to conclude that there is a cause-and-effect relationship between the set of essential features of the proposed technical solution and the achieved technical result.

The indicated features, which are distinctive from the prototype and which are covered by the requested scope of legal protection, are sufficient in all cases.

The objective of the proposed invention is to increase the reliability of the functioning of a guided projectile by ensuring reliable docking of the projectile with a tubular guide under combat conditions at various elevation angles while maintaining the possibility of using previously developed unguided and adjustable multiple launch rocket system projectiles.

A new set of essential features, as well as the presence of connections between them, allows, in part, due to:

- supplying the control system unit with a docking unit with ground equipment, designed to ensure the fixation of the projectile in the tubular guide - to ensure reliable interaction of the projectile with the tubular guide;

- the presence of a groove in the docking unit - to ensure fixation in the tubular guide, without the possibility of longitudinal movement of the projectile and eliminating the possibility of rotation in the guide after loading;

- the presence of an electrical connector - will ensure the connection of the electrical circuits of the projectile with the combat vehicle;

- making a docking unit with an outer diameter not exceeding the caliber of the projectile ensures loading into a tubular guide;

- location of the electrical connector at a distance of 0.8-0.85 of the projectile length from the axis of the drive pins - to ensure the possibility of electrical interaction of the projectile's on-board circuits with the launcher. If the electrical connector and pin axis are located at a distance greater than 0.85 of the projectile length, it will be impossible to launch previously created projectiles from the tubular guide. If the electrical connector and pins are located at a distance of less than 0.8 times the length of the projectile, the connections of the projectile blocks will not be controlled from unwinding, which will lead to the impossibility of loading or loading of a faulty projectile.

- making the angle between the axis of the electrical connector and the axis of the pins equal to 1.1-1.3 of the angle between the axis of the pins and the axis of the contact block - ensure fixation of the projectile in a given position. If the angular dimensions deviate from the specified values, the possibility of normal operation of the combat crew and the accomplishment of the assigned task is excluded. The selected angle ratio will preserve the ability to launch previously developed unguided and adjustable MLRS projectiles.

Making the angle between the axis of the electrical connector and the axis of the pins less than 1.1 of the angle between the axis of the pins and the axis of the contact block will provide fixation only for newly developed guided projectiles. The interaction of adjustable projectiles with a tubular guide designed for guided missiles is not ensured due to a change in the specified angular position at launch, which is necessary for the normal functioning of the projectile and separation of the warhead in flight.

Making the angle between the axis of the electrical connector and the axis of the pins more than 1.3 of the angle between the axis of the driving pins and the axis of the contact block will lead to a radial displacement of the tear-off connector into the area of the projectile's gravity, which will lead to possible destruction of the docking unit under the projectile's own weight.

The feature characterizing the proposed invention in a specific form allows, in part, due to:

- supplying the tubular guide of the guided missile with a finger to interact with the groove of the docking unit, the driving pins are configured to interact with the tubular guide and ensure rotation of the projectile around the longitudinal axis until the groove of the projectile docking unit interacts with a finger, the groove in the docking unit is designed to provide fixation in a tubular guide, without the possibility of longitudinal movement of the projectile and excluding the possibility of rotation in the tubular guide after loading - to ensure fixation of the projectile in the tubular guide under combat conditions at different elevation angles;

- flat pair contacts mounted on a contact block - increase the area of contacting surfaces and thereby ensure reliable contact with the mating elements of the combat vehicle.

The specified technical result is achieved by the fact that in guided missiles the projectile control system unit is equipped with a docking unit configured to ensure fixation of the projectile in a tubular guide, the docking unit contains a groove and an electrical connector, the electrical connector is made with an outer diameter not exceeding the caliber of the projectile, and fixed at a distance of 0.8-0.85 of the projectile length from the axis of the driving pins, and the smallest angle between the axis of the electrical connector and the axis of the pins is 1.1-1.3 angles between the axis of the pins and the axis of the contact block, the tubular guide is equipped with a finger for interaction with the groove of the docking unit, the driving pins are configured to interact with the tubular guide, and ensure rotation of the projectile around the longitudinal axis before the groove of the projectile docking unit interacts with a finger, the groove in the docking unit is designed to provide fixation in the tubular guide, without the possibility of longitudinal movement of the projectile and To eliminate the possibility of rotation in the tubular guide after loading, flat pair contacts are mounted on the contact block.

The essence of the invention is illustrated by the drawing, where figure 1 shows a general view of a guided missile launched from a tubular guide, figure 2 shows a cross-section of the projectile.

A guided missile launched from a tubular guide contains a control system unit 1 located in front of the warhead 2, a rocket engine 3, a nozzle block 4, with a contact block 5 placed on it and driving pins 6 interacting with the tubular guide 7. For interaction of the projectile with tubular guide 7, the control system block 1 is equipped with a docking unit 8, designed to ensure the fixation of the projectile in the tubular guide. The docking unit 8 contains a groove 9 and an electrical connector 10. The outer diameter d does not exceed the caliber of the projectile D. The electrical connector 10 is fixed to the control system unit 1 at a distance a - 0.8...0.85 of the projectile length L from the axis of the driving pins 6. α - the angle between the axis of the electrical connector 10 and the axis of the driving pins 6 is 1.1...1.3 β - the angle between the axis of the driving pins 6 and the axis of the contact block 5. In special cases, the tubular guide 7 is equipped with a pin 12 for interaction with the groove 9 of the node docking 8. The driving pins 6 are configured to interact with the screw groove 13 of the tubular guide 7 and ensure rotation of the projectile around the longitudinal axis until the groove 9 of the projectile docking unit 8 interacts with the finger 12. The groove 9 in the docking unit 8 is designed to provide fixation in the tubular guide 7, without the possibility of longitudinal movement of the projectile and excluding the possibility of rotation in the tubular guide 7 after loading. Flat contacts 11 are mounted on terminal block 5.

The described guided missile, launched from a tubular guide, operates as follows.

During the loading process, the rocket projectile is moved in a tubular guide 7. The driving pins 6, interacting with the screw groove 13 of the guide 7, ensure rotation of the projectile around the longitudinal axis until the groove 9 of the projectile docking unit 8 interacts with the mating element with the pin 12 placed on the guide 7. When the groove coincides 9 with the counter element finger 12 of the tubular guide 7, the projectile is secured against axial movement and rotation, which ensures the connection of the electrical connector 10. With the electrical connector 10 connected, the necessary checks are carried out and a command is given to launch the projectile. In turn, placing the axis of the electrical connector 10 from the axis of the drive pins at a distance of 3 provides control that prevents unwinding of the connections between the control system unit 1, the warhead 2, the rocket engine 3 and the nozzle unit 4, for example, which occurred during transportation. Angle α - ensures the interaction of the launch contacts with the power source located on the tubular guide, necessary to start the jet engine, which will retain the ability to launch previously developed unguided and adjustable MLRS projectiles. In particular cases, flat pair contacts 11 mounted on the contact block 5 provide reliable contact with the mating elements located on the tubular guide 7, necessary to issue a command to start the rocket engine 3.

The proposed technical solution made it possible to develop a guided missile that improves operational reliability by ensuring the projectile is docked with a tubular guide, and maintains the possibility of using previously developed unguided and adjustable MLRS projectiles.

This applied effect is confirmed by flight design tests of samples of guided missiles launched from a tubular guide, made in accordance with the proposed invention.

Currently, design documentation has been developed and full-scale testing of prototypes has been completed.

Claims (2)

1. A guided missile launched from a tubular guide, containing a control system unit located in front of the warhead, a rocket engine, a nozzle block with a contact block placed on it and drive pins interacting with the tubular guide, characterized in that the projectile control system unit is also equipped with a docking unit configured to ensure fixation of the projectile in the tubular guide, the docking unit contains a groove and an electrical connector, the tubular guide is equipped with a pin to interact with the groove of the docking unit, the driving pins are configured to interact with the tubular guide and ensure rotation of the projectile around the longitudinal axis up to interaction of the groove of the projectile docking unit with the pin, the groove in the docking unit is designed to ensure fixation of the projectile in the tubular guide, without the possibility of longitudinal movement of the projectile and excluding the possibility of its rotation in the tubular guide after loading, the electrical connector is made with an outer diameter not exceeding the caliber of the projectile, the electrical connector is fixed at a distance of 0.8-0.85 of the projectile length from the axis of the driving pins, and the angle between the axis of the electrical connector and the axis of the pins is 1.1-1.3 of the angle between the axis of the pins and the axis of the contact block. 2. A guided missile according to claim 1, characterized in that flat pair contacts are mounted on the contact block.

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