RU2767645C1 - Anti-aircraft guided missile 9m96 - Google Patents

Abstract

FIELD: weapons.

SUBSTANCE: invention relates to the field of military equipment, namely to missiles with a gas-dynamic control system, and can be used in the development of guided missiles, anti-missiles and ballistic missiles. Missile comprises body (1) accommodating power supply system, combat equipment, control system hardware, cruise propulsion system and transverse control propulsion system (3). Transverse control propulsion system (3) consists of a gas generator connected to nozzles (4) located in the equatorial plane of the rocket in the centre of its mass (2). Nozzles (4) are closed by covers, which have independent opening. Control system provides transverse thrust effect on rocket of design value due to simultaneous opening of two nozzles of propulsion system of transverse control (3), which total thrust is directed along bisector of angle between axes of connected nozzles and is proportional to double cosine of half of angle between axes of connected nozzles. When the preset transverse displacement of the missile is achieved to compensate for the miss relative to the target, the control system provides the creation of the opposite thrust of the propulsion system due to simultaneous opening of nozzles of propulsion system of transverse control (3), opposite to previously opened nozzles, total thrust of which compensates thrust of previously opened nozzles.

EFFECT: controllable change in the trajectory of movement of the centre of mass of the missile is provided without changing the angular position of the construction axis of the missile in pitch and heading, which improves the dynamics of the missile, reduces fuel consumption, makes it possible to use rocket fuel with limiting value of specific impulse in transverse control propulsion system.

1 cl, 1 dwg

Description

The field of technology to which the invention belongs.

The invention relates to the field of military technology, namely missiles with a gas-dynamic control system, and can be used in the development of guided missiles, anti-missiles and ballistic missiles.

The level of technology.

Known designs of missile control and stabilization systems:

- Karpenko A.V. Russian missile weapons 1943-1993, reference book, second edition, St. Petersburg, "PIKA", 1993, pp. 135, 145, 146;

- Russian air defense aviation and scientific and technological progress: Combat complexes and systems yesterday, today, tomorrow / ed. E.A. Fedosova, M., Drofa, 2001, pp. 214, 215, 282, 286-290;

- RF patent RU 2327949 Cl, F42B 15/00, publication date 06/27/2008;

- RF patent RU 2380651 Cl, F42B 15/00, publication date 27.01.2010;

- US patent US 20040084564 Al, F42B 15/00, publication date 05/06/2004;

- US patent US 20050011989 Al, F42B 15/00, publication date 01/20/2005;

- Patent No. RU 2548957 Cl, F42B 15/00, publication date 04/20/2015.

A common disadvantage of these inventions, in our opinion, is the need to use additional acceleration of the rocket in the guidance area. Such a design of the rocket provides an increase in available overloads in the target area at high altitudes from 30 to 40 km due to the projection of the rocket engine thrust on the normal to its velocity vector and an increase in velocity head due to an increase in the rocket flight speed in the target area.

However, at high altitudes the efficiency

aerodynamic rudders inevitably decreases, which leads to a slow exit of the rocket to the required angles of attack and, accordingly, to a decrease in the probability of hitting the target. When attacking atmospheric targets, aerodynamic rudders become completely ineffective.

As a close analogue of the invention, the technical solution proposed in the RF patent - "Device for controlling a highly maneuverable rocket", patent No. RU 2146353 Cl, publication date 10.03.2000, can be considered. The positive effect of this technical solution in comparison with analogues is achieved by the fact that in a rocket containing a homing head, a control unit, a sustainer engine, aerodynamic ailerons installed in the nose of the rocket outside the impact zone of the outflowing jet of the transverse control engine, aerodynamic surfaces installed in the tail of the rocket, a transverse control engine with at least two gas generators and radial nozzles is used, mounted on bearings and rotating relative to the longitudinal axis of the rocket with a special drive, characterized in that the radial angle between adjacent nozzles of the transverse control engine, multiplied by an integer, is 90 ° , a squib is connected to each plug connected by a communication line to the output of the control unit, and the aerodynamic surfaces are fastened to the outer ring of the bearing, the inner ring of which is fixed to the main engine gas duct.

The disadvantages of a close analogue of the invention are:

- testing of a missile miss relative to the target is carried out by a transverse control engine in the form of a separate missile compartment, the longitudinal axis of which is mounted on a bearing to ensure the rotation of the transverse control engine compartment relative to the longitudinal axis of the missile according to the signals from the control unit, which significantly complicates the design of the missile and labor costs for its manufacture. The rotation of the transverse control engine compartment is carried out relative to other rocket compartments, which rotate in the opposite direction and which are not fixed in space in the description of the invention;

- control of the direction vector of the transverse movement of the missile is carried out by rotating the transverse control engine compartment relative to other missile compartments with a special drive, which additionally increases the time constant of the rocket's response to the control action by increasing the moment of inertia and the mass of the rotary parts of the rocket;

- execution of the transverse control engine as part of at least two autonomous gas generators, each gas generator containing its own crown of radial nozzles located near the center of mass of the rocket and, if necessary, connected to the combustion chamber by a gas conduit, which not only complicates the design of the transverse control engine, but also removes the nozzles of the lateral control engine of both the first and second rims from the exact location in the center of mass of the rocket, which causes the eccentricity of the applied lateral control forces, however, special eccentricity compensation devices that prevent the rocket from turning at the angles of course and pitch are not provided in the invention.

These shortcomings reduce the dynamics of the rocket during the turn of the rocket in the direction of the target and, as a result, cause increased missile misses relative to the target and increased fuel (working fluid) consumption.

As a prototype of the invention, the technical solutions set forth in the article “Get in the warhead: Triumph”, https://www.popmech.ru/weapon/8210-popast-v-boegolovku-triumf/, date of posting on the site 04.06, can be considered. 2016. The positive effect of this technical solution in comparison with analogues is achieved by the fact that in a rocket containing a body, a control system, combat equipment and an autonomous propulsion system, a gas-dynamic method of controlling the missile using an autonomous transverse control propulsion system is implemented. It is used in the final phase of guidance, when there is reliable information about the position of the target. The gas-dynamic control system is a propulsion system, the nozzles of which are located along the circumference of the missile defense system in the region of the center of mass.

The disadvantages of the prototype of the invention are:

1) in the case of using a plurality of rocket engines of a traditional design (example: ERINT rocket - 180 radially arranged impulse rocket engines - 10 rings of 18 engines each) - this is the impossibility of controlling the thrust of transverse control engines depending on the realized miss and the temperature of the solid fuel charge, thrust spread individual engines due to natural causes of individual production;

2) when using engines with controlled gas supply (example: Aster rocket - transverse control propulsion system is made in the form of a solid propellant gas generator with four slotted nozzles equipped with control valves):

- the use of special valve mechanisms made of refractory materials, traditionally expensive and difficult to obtain and process;

- limitation of the specific impulse of the engine due to the impossibility of using fuel with a combustion temperature exceeding the thermal stability of existing structural materials.

Disclosure of the essence of the invention.

The rocket contains a body, military equipment placed in it, control system equipment and a transverse control propulsion system, consisting of a gas generator, and a large number of nozzles connected to the gas generator, closed by covers that have independent opening, and the transverse control propulsion system nozzles are located in the center of mass rockets and provide a change in the trajectory of movement of only the center of mass of the rocket without changing the angular position of its building axis in pitch and course and using aerodynamic forces or thrust of a sustainer propulsion system with a longitudinal nozzle to target the target.

The control system provides thrust control of the propulsion system by opening the nozzles of the transverse control propulsion system according to the commands of the missile control system.

The control system provides a transverse thrust effect on the rocket of the calculated value to compensate for the miss realized under specific conditions by simultaneously opening two nozzles of the transverse control propulsion system, the total thrust of which is directed along the bisector of the angle between the axes of the included nozzles and is proportional to the doubled cosine of half the angle between the axes of the included nozzles.

When a predetermined lateral displacement of the missile is reached to compensate for the miss of the missile relative to the target, the control system ensures the creation of the opposite thrust of the propulsion system due to the simultaneous opening of the nozzles of the propulsion system of the lateral control opposite to the previously open ones, the total thrust of which compensates for the thrust of the previously opened nozzles.

The positive effect of the proposed technical solution is to improve the dynamics of the rocket due to the exclusion from the generalized time constant of the reaction of the rocket to the control action of the time component necessary to turn the rocket in elevation or course, the absence of the need for constant operation of the rocket propulsion systems (longitudinal and transverse), reduction due to this total fuel consumption (working fluid), equality of thrust of each of the opening nozzles due to their supply from one gas generator, control of the magnitude and direction of the lateral force of the transverse control propulsion system without the use of a valve system operating in hot gas, as a result of this, the possibility of using in a propulsion system transverse control of propellant with a limit value of the specific impulse.

Implementation of the invention.

An exemplary embodiment of the invention is shown in FIG. 1 where:

1. Rocket body.

2. The center of mass of the rocket.

3. Transverse control propulsion system.

4. Nozzles of the transverse control propulsion system.

5. Thrust vector of the first nozzle.

6. Thrust vector of the second nozzle.

7. The resulting thrust vector of the transverse control propulsion system.

Claims (1)

A missile containing a body, a power supply system, combat equipment, control system equipment, a marching propulsion system and a transverse control propulsion system, characterized in that the transverse control propulsion system consists of a gas generator connected to nozzles in the equatorial plane of the rocket in the center of its mass , the nozzles are closed with covers that have independent opening, the control system provides a transverse thrust effect on the rocket of the calculated value by simultaneously opening two nozzles of the transverse control propulsion system, the total thrust of which is directed along the bisector of the angle between the axes of the included nozzles and is proportional to twice the cosine of half the angle between the axes enabled nozzles, upon reaching a predetermined transverse displacement of the missile to compensate for the miss relative to the target, the control system provides the creation of the opposite thrust of the propulsion system due to the simultaneous opening of the engine nozzles lateral control installation, opposed to the previously opened ones, the total thrust of which compensates for the thrust of the previously opened nozzles.

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