RU2600187C2 - Solid propellant rocket engine - Google Patents

Abstract

FIELD: rocket technics.

SUBSTANCE: invention relates to rocket engineering and can be used during development of a solid propellant rocket engine for an aircraft having overall size limitations in the initial state, with a payload, the length of which is comparable with the length of the rocket engine housing. Solid propellant rocket engine comprises a housing, in the inner cavity of which there is a charge, a nozzle and a front cover made in the form of a jar, the inner cylindrical surface of which contacts with a piston installed with the possibility of longitudinal movement. On the piston by means of securing assemblies a payload is fixed. Between the piston and the jar bottom a pressure accumulator is arranged, and on the open end of the jar there is a thrust collar. Pressure accumulator is designed to create a pressure in the jar exceeding the one calculated for the jar shell by a value equal to or less than the pressure created in the housing inner cavity due to the charge combustion.

EFFECT: invention provides decreased weight and reliability of a solid propellant rocket engine.

1 cl, 2 dwg

Description

The invention relates to rocket technology and can be used to create a solid propellant rocket engine (solid propellant rocket engine) of an aircraft having overall limitations in the initial state, with a payload accelerated by a solid propellant rocket engine (capsule with devices or a projectile, or solid propellant rocket engine of the next stage), and the useful length load is comparable with the length of the body of the solid propellant rocket engine.

Known aircraft containing solid propellant rocket engine, in the cavity of the front cover of which is made in the form of a glass, to reduce the dimensions of solid rocket motor and the aircraft as a whole partially (in length) placed payload accelerated by solid rocket engine (patent RU 2222771 C1, F42B 15/00, publ. January 27, 2004, Bulletin No. 3). The disadvantage of this device is that the payload is not completely placed along the length in the glass cavity, but only by its stern, which does not allow to fully reduce the length of the aircraft.

In a solid propellant rocket engine (US Pat. No. 6,647,889), comprising a housing in which an internal charge is placed, a nozzle, a front cover made in the form of a cup, with a piston mounted with the possibility of longitudinal movement in contact with the piston by means of fixation units a payload is fixed, and a pressure accumulator is installed between the piston and the bottom of the cup, and a thrust shoulder is installed on the open end of the cup, the problem of reducing the length is solved. However, the disadvantage of this aircraft is the increased mass of the glass, the cylindrical shell of which is designed to work not only under the influence of pressure from the inside, but also under the influence of external (relative to the glass) internal chamber pressure that occurs in the housing during the operation of the solid propellant rocket engine.

A decrease in the mass of the cup is achieved in a rocket engine of solid fuel containing a housing in which the charge is placed in the inner cavity, a nozzle, a front cover made in the form of a cup, with a piston mounted with the possibility of longitudinal movement in contact with the cylindrical surface, fixed to the piston by means of fixing units payload, and a pressure accumulator is installed between the piston and the bottom of the cup, and a thrust shoulder is installed on the open end of the cup, while the pressure accumulator is Designed to create pressure in a glass that exceeds the pressure for which the housing is designed (patent RU 2558488 C2, F02K 9/08, published on 08/10/2015, bull. No. 22). However, the disadvantage of this rocket engine of solid fuel is the low reliability associated with the possibility of destruction of the housing due to the lack of limitation of the maximum pressure in the glass created by the pressure accumulator.

The specified rocket engine of solid fuel is technically the closest to the proposed invention and adopted as a prototype.

The invention was tasked with reducing weight and increasing the reliability of the aircraft.

EFFECT: reduced mass and increased reliability of a solid fuel rocket engine.

The technical result is achieved due to the fact that in the rocket engine of solid fuel containing a housing in the inner cavity of which a charge is placed, a nozzle, a front cover made in the form of a cup, with a piston mounted with the possibility of longitudinal movement in contact with the piston, mounted with the possibility of longitudinal movement by means of fixation nodes, a payload is fixed, and a pressure accumulator is installed between the piston and the bottom of the cup, and a persistent shoulder is installed on the open end of the cup, the pressure Ia is designed to create a pressure in the glass that exceeds the pressure to which the shell is calculated glass by an amount equal to or less than the pressure generated in the internal body cavity due to charge combustion.

In FIG. 1 shows a longitudinal section of a solid propellant solid propellant rocket in its initial state; in FIG. 2 - longitudinal section of the solid propellant rocket engine in flight (working) configuration with extended payload.

The rocket engine of solid fuel contains a housing 1, in the inner cavity 2 of which a charge 3 is placed, a nozzle 4 and a front cover 5. The front cover 5 is made in the form of a glass 6 placed inside the charge channel 3. The glass 6 contains a cylindrical shell 7, bottom 8 and open end face 9. In the barrel 6, a piston 10 is mounted with the possibility of longitudinal movement, which contacts the inner cylindrical surface 11 of the barrel 6. On the piston 10, nodes 12 for fixing the payload 13 are made. A pressure accumulator 14 is installed between the piston 10 and the bottom 8 of the barrel 6. . The pressure accumulator 14 is designed to create a pressure in the glass 6, which exceeds the pressure for which the shell of the glass is designed, by an amount equal to or less than the pressure created in the internal cavity of the housing due to the burning of the charge.

The device operates as follows.

Before starting the solid propellant rocket motor, a command is issued to operate the pressure accumulator 14. Under the action of the pressure accumulator 14, the pressure inside the nozzle 6 increases, acting on the piston 10. Together with the payload 13, the piston 10 moves all the way to the stop shoulder 15. Thus, the aircraft is transferred from its initial position to the flight configuration. Further operation of the pressure accumulator 14 provides pressurization inside the cup 6, which exceeds the pressure in the inner cavity 2 of the housing 1 during operation of the solid propellant rocket motor by no more than the pressure in the cup for which the cup shell is designed.

Then a command is issued to start the solid propellant rocket motor. In the internal cavity 2 of the housing 1, the pressure increases due to the burning of the charge 3. The solid propellant rocket motor starts to work, dispersing the payload 13. The combined action of the pressure created by the pressure accumulator 14 and the external (relative to the cup) internal chamber pressure that occurs in the housing during the solid propellant rocket motor provides strength unloading glasses 6.

Claims (1)

A solid propellant rocket engine containing a housing in which an internal charge is placed, a nozzle, a front cover made in the form of a cup, with a piston mounted with the possibility of longitudinal movement in contact with the internal cylindrical surface, a payload is fixed to the piston by fixation units, and between a pressure accumulator is installed by the piston and the bottom of the cup, and a persistent flange is installed on the open end of the cup, characterized in that the pressure accumulator is designed to create a pressure in a glass, exceeding the pressure for which the shell of the glass is designed, by an amount equal to or less than the pressure created in the internal cavity of the housing due to the combustion of the charge.

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