RU2790656C1 - Supersonic guided missile - Google Patents

Abstract

FIELD: supersonic guided missile.

SUBSTANCE: supersonic guided missile, configured according to the aerodynamic “canard” design, comprises blade stabilizers, a cruise engine, a nozzle block, a body with a pointed nose part with aerodynamic rudders placed thereon, and a control system. The launching stage is mounted on the nozzle block. The launching stage contains a solid-propellant rocket engine, a gas-dynamic actuator with nozzles located on the side surface perpendicular to the longitudinal axis of the projectile, and an attachment unit connecting the launching stage and the nozzle block. The separation of the starting stage occurs due to the destruction of the attachment unit under the influence of the pressure generated by the combustion products of the cruise engine on the front end of the launching stage after launch of the stage.

EFFECT: increasing the grouping and accuracy of firing a supersonic guided missile.

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Description

The invention relates to the field of rocket technology, and in particular to guided missiles of multiple launch rocket systems.

The object of the invention is a supersonic guided missile made according to the "duck" aerodynamic configuration, containing bladed stabilizers, a sustainer engine, a nozzle block, a body with a pointed nose, aerodynamic rudders placed on it and a control system.

Multiple launch rocket systems (MLRS) are widely used to combat various ground targets. The composition of such systems includes rockets equipped with a monoblock or cluster warhead, a solid rocket engine and an aerodynamic stabilizer.

Thus, modern conditions for resolving military conflicts dictate the requirements for modern ammunition and complexes. One of the most important requirements for weapons is the time factor for striking. Therefore, supersonic rockets are often used for operational destruction.

Currently, to improve the accuracy of firing, various systems for controlling the movement of rockets are used, which make it possible to improve these characteristics in comparison with unguided projectiles.

A rocket is known according to the patent of the Russian Federation 2125701 (IPC F42B 10/00, publ. 27.01.1999). When the rocket is launched, the gas-dynamic system of angular stabilization creates control forces that compensate for the impact of initial disturbances and wind loads.

This technical solution provides an increase in firing accuracy through the use of a gas-dynamic system of angular stabilization.

Common features with the projectile proposed by the authors are the presence of a cylindrical body with a front pointed conical part, a rocket engine, a tail and a gas-dynamic angular stabilization system with nozzles.

The disadvantages of the known missiles include the impossibility of correcting the trajectory, since the system of angular stabilization of the rocket provides only the correction of the initial perturbations when leaving the guide.

A rocket with a detachable engine is known according to RF patent 2233424 (MPK F42B 15/10, publ. 27.07.2007, BI No. 21). At the same time, a special structural element is used to separate the engine, containing a cavity in which a powder charge is placed to separate the starting and starting the sustainer engine, which complicates the design and reduces the reliability of the projectile.

The closest in technical essence to the rocket proposed by the authors is a supersonic guided rocket according to the patent of the Russian Federation 2459177 (MPK F42B 15/00, F42B 10/38, publ. 08.20.2012, BI No. "duck" scheme, containing a body with a pointed nose, a stabilizer made in the form of drop-down blades, a main engine, aerodynamic controls - rudders mounted on the bow of the body and a control system.

This rocket is supersonic due to the special shape of the airframe, namely the shape of the nose, which is made with a power-law profile that provides the least aerodynamic drag when flying at supersonic speeds.

The purpose of the invention (prototype) was to create an optimal geometric shape of the bow and aerodynamic control surfaces, which increases the aerodynamic characteristics of the rocket.

During the operation of such a guided missile, its maneuverability is limited by the area of plumage and the speed of the oncoming flow. And while the rocket has not yet gained sufficient speed, aerodynamic rudders are not effective enough to extinguish starting disturbances, including fluctuations in the launch guide.

Common features with the design of the supersonic guided missile proposed by the authors are the aerodynamic design of the "duck", the body with a pointed nose, aerodynamic rudders, the control system, the sustainer engine, which provides acceleration to supersonic speed, its nozzle block, bladed stabilizers placed on it.

Unlike the prototype, on the nozzle block of the inventive projectile, a starting stage is fixed, containing a mount connecting it and the nozzle block, a gas-dynamic actuator with nozzles located on the side surface perpendicular to the longitudinal axis of the projectile and a solid-propellant rocket engine with a nozzle directed along the longitudinal axis of the projectile, with In this case, the separation of the starting stage occurs due to the destruction of the attachment point under the influence of the pressure of the combustion products of the propulsion engine on the front end of the starting stage after its launch.

The indicated features, which are different 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 accuracy and accuracy of fire by increasing the reliability of the functioning of a rocket projectile with a gas-dynamic stabilization system by providing a maximum gas-dynamic stabilizing moment relative to the center of mass of the projectile, as well as reducing the mass by separating the used launch stage.

The specified technical result is achieved by the fact that, unlike the prototype, the supersonic guided missile is equipped with a launch stage, which ensures its precise spatial positioning on the flight mission trajectory and its angular stabilization at the time of launching its sustainer engine. The starting stage is fixed by means of a mount on the nozzle block of the supersonic guided missile and contains a solid-propellant rocket engine and a gas-dynamic actuator with nozzles located on the side surface perpendicular to the longitudinal axis of the projectile. According to the signals from the control system of the supersonic missile, the gas-dynamic actuator, using nozzles located on the side surface perpendicular to the longitudinal axis of the projectile, creates control moments that bring it to the firing trajectory. Due to the large distance between the points of application of reactive forces acting perpendicular to the longitudinal axis of the projectile relative to the center of gravity, the spatial positioning time is reduced, reducing its fluctuations, which leads to angular stabilization at the time of launching its sustainer engine, increasing the accuracy and accuracy of fire, while the separation of the starting stage from the nozzle block of the rocket is carried out by destroying the attachment unit connecting it and the nozzle block under the influence of the pressure of the combustion products of the propulsion engine on the front end of the starting stage after its launch.

The mount is located in the tail section of the supersonic missile and is located on the body of the nozzle block. The front end of the starting stage is made in the form of a glass with a blank bottom, which is attached, for example, by stringing with a sliding fit on the nozzle block and then installed and fixed with a fastener, for example, in the form of screws or pins.

A new set of structural elements, as well as the presence of links between the parameters of the claimed supersonic guided missile made it possible, in particular, due to:

- fixing the launch stage, containing the attachment point connecting it and the nozzle block, a gas-dynamic actuator with nozzles located on the side surface perpendicular to the longitudinal axis of the projectile and a solid-propellant rocket engine with a nozzle directed along the longitudinal axis of the projectile impact on the rocket projectile, providing the maximum gas-dynamic control moment, in contrast to the rocket projectile with no gas-dynamic stabilization system, due to the placement of the launch stage in the tail section of the rocket projectile at a great distance from the center of mass of the projectile, and therefore increase the accuracy and accuracy of fire due to increase the reliability of operation at the starting section of the trajectory at the moment of movement of the rocket at low speed, when the oncoming flow is not enough for the operation of aerodynamic rudders, as well as to exclude the negative impact of the turbulent flow of the jet of the gas-dynamic actuator on the aerodynamic characteristics of the stabilizer, and therefore improve the aeroballistic characteristics of the projectile;

- separation of the launch stage from the nozzle block due to the destruction of the attachment point under the influence of the pressure on the front end of the launch stage of the combustion products of the sustainer engine after its launch;

- the presence of a solid-propellant engine as part of the launch stage;

- the presence of a gas-dynamic actuator as part of the launch stage; speed, when the oncoming flow is not enough for the operation of aerodynamic rudders, providing the maximum gas-dynamic control moment, in contrast to a rocket with no gas-dynamic stabilization system, minimizing the time of spatial positioning, reducing its fluctuations due to the location of the points of application of reactive forces with a large distance relative to the center masses of the projectile acting perpendicular to the longitudinal axis.

The features that characterize the invention in specific forms of execution are provided, in particular, due to:

- making the bladed stabilizer collapsible with the possibility of opening after separation - to increase the sensitivity of the projectile to the effects of gas-dynamic controls due to the absence of a stabilizing moment in the initial section of the trajectory, to exclude the aggressive effect of combustion products from the starting engine and to protect the stabilizers from mechanical damage when moving in the launch guide;

- placement of an additional control system that issues commands to the gas-dynamic actuator, an attachment unit connecting the launch stage with the main engine nozzle block the bow of the missile due to the transfer of part of the functions to the control system of the starting stage.

The foregoing allows us to conclude that there is a causal relationship between the set of essential features of the proposed technical solution and the achieved technical result.

The essence of the invention is illustrated by the drawing, where in Fig. 1 shows a general view of a supersonic guided missile, FIG. 2 - attachment point (enlarged), in Fig. 3 - location of control systems and folding stabilizers.

The supersonic guided missile contains blade stabilizers 1, a propulsion engine 2, a nozzle block 3, a body with a pointed nose 4, aerodynamic rudders 5, a control system 6, a launch stage 7, a solid propellant rocket engine 8, a gas-dynamic actuator 9, a launch stage mount 10, the front end of the launch stage 11, perpendicular to the longitudinal axis of the projectile nozzle 15.

In special cases of execution, a supersonic guided missile contains:

- folding stabilizers 12 with the possibility of unfolding after separation of the starting stage 7;

- an additional control system 14, the operation of which is synchronized before launch with the control system 6. In this case, the control system 14 generates commands and sends signals to the gas-dynamic actuator 9 and to nozzles 15 perpendicular to the longitudinal axis of the projectile, solid rocket engine 8 and main engine 2, and the control system 6 generates commands and sends signals to the aerodynamic rudders 5, ensuring the launch of the missile on the trajectory according to the flight task.

Supersonic guided missile works as follows. During pre-launch preparation, flight task data is entered into the control system 6. After starting the solid-propellant rocket engine 8 of the starting stage 7, the rocket begins to move at subsonic speed, after leaving the launch guide, according to signals from the control system 6 of the supersonic rocket, the gas-dynamic actuator 9, using nozzles 15 located on the side surface perpendicular to the longitudinal axis of the projectile, creates a stabilizing moment , which compensates for negative firing parameters (for example, side wind, fluctuations in the launch guide and rocket engine thrust eccentricity) at the starting section of the trajectory. Due to the large distance between the points of application of reactive forces acting perpendicular to the longitudinal axis of the projectile relative to the center of gravity, the time of spatial positioning is reduced, reducing its fluctuations, which leads to acceleration of angular stabilization compared to the action of aerodynamic stabilizers 1, when there is not enough speed of the oncoming flow. When the supersonic guided missile achieves the specified trajectory and spatial parameters, the control system 6 gives a command to start the sustainer rocket engine 2, under the influence of pressure from the combustion products on the front end 11, the attachment assembly 10 is destroyed (for example, forcing elements in the form of pins or screws) and separated starting stage 7. Further, during the operation of the propulsion rocket engine 2, the rocket reaches supersonic speed, while the control system 6 provides control of the aerodynamic rudders 5 according to the flight task data until the target is reached.

The proposed technical solution made it possible to develop a supersonic guided missile of increased accuracy and accuracy by increasing the reliability of the missile by providing the maximum gas-dynamic stabilizing moment relative to the center of mass of the projectile, as well as reducing the mass by separating the used launch stage.

The bench tests of the experimental sample with imitation of disturbing influences at the initial stages of the operation of the launch stage and the process of its separation from the propulsion engine demonstrated full compliance with the features declared by the authors, solving the problem of the invention. In addition, full-scale tests of the invention, manufactured in accordance with the formula, in the conditions of the landfill showed positive results.

Currently, design and technological documentation has been developed, prototypes have been made, tests have been carried out, and production of devices in accordance with the invention is planned.

Claims (3)

1. Supersonic guided missile, made according to the aerodynamic "duck" scheme, containing bladed stabilizers, a main engine, a nozzle block, a body with a pointed nose, aerodynamic rudders placed on it and a control system, characterized in that the starting stage is fixed on the nozzle block , containing the attachment unit connecting it and the nozzle block, a gas-dynamic actuator with nozzles located on the side surface perpendicular to the longitudinal axis of the projectile, while the separation of the starting stage occurs due to the destruction of the attachment unit under the influence of the front end of the starting stage of the pressure of the combustion products of the propulsion engine after its launch . 2. A supersonic guided missile according to claim 1, characterized in that the bladed stabilizers are made collapsible with the possibility of opening after separation of the launch stage. 3. A supersonic guided missile according to claim 1, characterized in that it contains an additional control system that issues commands to the gas-dynamic actuator, an attachment unit connecting the launch stage with the main engine nozzle block.

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