RU2790728C1 - Cruise missile - Google Patents

Abstract

FIELD: rocket technology.

SUBSTANCE: rocket technology that can be used to create cruise missiles designed to destroy ground and surface targets. Cruise missile has a three-stage layout. The booster stage contains a solid propellant rocket engine (SPRE). The cruise stage contains a folding delta wing and tail assembly, a solid propellant gas generator, an afterburner and a ramjet engine. The combat stage contains a combat unit, an instrument compartment, a solid propellant rocket motor, a powder pressure accumulator and a nose cone with a solid propellant rocket motor.

EFFECT: reliable overcoming by the cruise missile of the enemy's anti-aircraft and anti-missile defense systems and hitting the target is achieved.

1 cl, 5 dwg

Description

The invention relates to the field of rocket technology, and can be used to create cruise missiles designed to destroy ground and surface targets.

A hypersonic cruise missile is known, consisting of a solid-propellant booster stage and a sustainer stage, which includes two modules, the first of which is combat and is made in the form of a glider, and the second is in the form of a power plant module with a hypersonic ramjet engine (scramjet engine). ), fixed under the fuselage of the combat module in a batch (parallel) scheme with the possibility of its separation in flight (patent No. 2579409, IPC: F42B 15/00 - prototype).

The main disadvantage of the well-known hypersonic cruise missile is the reduction in the flight speed of the combat module when planning to the target.

The objective of the invention is to eliminate this disadvantage and to ensure that the cruise missile reliably overcomes the enemy's air defense and missile defense systems and hits the target.

The solution to this problem is achieved by the fact that the proposed cruise missile contains a launch stage (SRS) with a solid propellant rocket engine (SSRM), a sustainer stage consisting of a body made in the form of a cylindrical shell on the outer surface of which a folding delta wing and a tail plumage located inside the body of a solid fuel gas generator having a torus shape and containing a charge of end combustion, and a glass forming an annular afterburner chamber of a rocket-ramjet engine (RPM) with the gas generator and connected to it by means of pylons, while a piston interacts with the inner cylindrical surface of the glass , mounted with the possibility of longitudinal movement, and a combat stage fixed on the end of the piston and consisting of a controlled combat unit (UBB), an instrument compartment and a solid propellant rocket engine, and a powder pressure accumulator (PAD) is installed between the bottom of the glass and the piston, and fixed on the open end of the glassa cone in front of which is a solid propellant rocket motor.

The proposed design of the cruise missile, due to its distinctive features, allows you to solve the set technical problems.

The essence of the invention is illustrated by drawings, where figure 1 shows a General view of the cruise missile before the start of work, figure 2 shows the moment of separation of the SRS after the end of the solid propellant; figure 3 - shows the moment of separation of the cone after the end of the RPD gas generator; figure 4 - shows the moment after the release of the combat stage and the piston with PAD from the glass; figure 5 shows the moment of separation of the UBB.

The cruise missile contains SRS 1, sustainer stage 2 and combat stage 3.

SRS 1 is connected to the sustainer stage 2 and contains solid propellant rocket engine 4.

The sustainer stage 2 consists of a housing 5 made in the form of a cylindrical shell and inside of which a solid propellant gas generator 6 and a cup 7 are located, forming an annular afterburner chamber 8 RPD 9. Using pylons 10 and 11, the gas generator 6 is connected to the cup 7. On the outer The surface of the housing 5 is fixed with a folding delta wing 12 and tail 13. The gas generator 6 has a torus shape and contains an end combustion charge 14. A piston 15 is installed inside the cup 7 with the possibility of longitudinal movement. A PAD 17 is installed between the bottom 16 of the cup 7 and the piston 15.

At the open end of the glass 7, a cone 18 is fixed, in the front part of which the solid propellant rocket motor 19 is located.

Combat stage 3, fixed on the end of the piston 15, includes UBB 20, instrument compartment 21 and solid propellant rocket engine 22.

The proposed cruise missile functions as follows.

After separation from the carrier, the solid propellant rocket engine 4 CPC 1 is launched, which ensures the launch of the cruise missile to the cruising speed and flight altitude. Upon completion of the operation of the solid propellant rocket engine 4, the SRS 1 is separated and at the same time the end combustion charge 14 is ignited, located in the gas generator 6. The products of primary combustion of solid fuel formed in the gas generator 6 enter the annular afterburner chamber 8 RPD 9, where they burn out in the air entering from the environment, thus creating traction. After the release of RPD 9 to the nominal mode of operation, the cruising flight of the cruise missile begins.

When approaching the target, the RPD 9 is turned off and the solid propellant rocket engine 19 is launched, which ensures the reset of the cone 18. Then the PAD 17 is activated and the combustion products flowing from it fill the volume between the bottom 16 of the cup 7 and the piston 15. Under the gas pressure, the piston 15 moves in the cup 7 and pushes combat stage 3 out of it.

After the separation of the combat stage 3 from the sustainer stage 2, the solid propellant rocket motor 22 is launched. At the end of the solid propellant rocket motor 22, the UBB 20, which has reached hypersonic flight speed, is separated. Next, the UBB 20 swoops down on the target.

The use of the proposed technical solution will make it possible to reliably overcome the enemy's anti-aircraft and anti-missile defense systems and hit the target.

Claims (1)

The cruise missile contains a booster stage (SRS) with a solid propellant rocket engine (SSRM), a sustainer stage consisting of a body made in the form of a cylindrical shell, on the outer surface of which a folding delta wing and tail unit are fixed, located inside the body of the solid propellant gas generator, having a torus shape and containing a charge of end combustion, and a glass forming an annular afterburning chamber of a rocket-ramjet engine (RPD) with a gas generator and connected to it by means of pylons, while a piston installed with the possibility of longitudinal movement interacts with the inner cylindrical surface of the glass, and a combat stage fixed on the end of the piston and consisting of a controlled combat unit (UBB), an instrument compartment and a solid propellant rocket engine, and a powder pressure accumulator (PAD) is installed between the bottom of the glass and the piston, and a cone is fixed on the open end of the glass, in front of which the solid propellant rocket engine is located .

Images