RU2685751C1 - Rocket engine of solid fuel - Google Patents

Abstract

FIELD: rocket equipment.SUBSTANCE: invention relates to rocket engineering, particularly, to solid-propellant rocket engines, and can be used in missiles for various purposes. Solid-propellant rocket engine includes housing with front bottom, igniter and solid fuel charge in form of cylindrical body with central channel, arranged in housing, in rear part of which multi-nozzle unit is installed. Solid-fuel charge is equipped with peripheral through channels, and ends of solid fuel charge are armored with diaphragms of incombustible material with low heat conductivity. Through holes are made in diaphragms and coaxial with channels of solid fuel charge and nozzles of multi-nozzle unit installed without clearance relative to diaphragm in lower part of rocket engine. Front bottom is made with recess on inner surface, by means of which peripheral solid fuel charge channels are interconnected.EFFECT: invention allows increasing specific impulse of rocket engine with multi-nozzle unit.1 cl, 3 dwg

Description

The claimed technical solution relates to rocket technology, in particular, to rocket engines of solid fuel, and can be used in rockets for various purposes.

Known rocket engine solid fuel, comprising a housing, an igniter, a nozzle bottom with a plurality of nozzles located around the circumference, a channel charge of solid fuel firmly attached to the housing, the charge has a channel that passes into the slit part with a plurality of slit slots, each of which faces the nozzle bottom and made with a plot expanding towards the end of the charge, with the number of slotted slits equal to the number of nozzles whose axes are located in the planes of symmetry of the slit slots passing through the cancer axis of this engine (patent RU No. 2344309, published January 20, 2009 Bull. No. 2).

Also known is a rocket engine of solid fuel, comprising a housing with a front bottom and a multi-nozzle block, an igniter and a powder charge in the form of a cylindrical body with a central bore (patent RU No. 159486, published 02.02.2016 Bull. No. 4). Deposit powder charge is installed in the body with a uniform gap between the body and the powder charge and fixed spacers of slowly burning materials.

A disadvantage of the known technical solutions is the low value of the specific impulse of the rocket engine. This is due to the fact that the pressure that is created in the combustion chamber during the combustion of solid fuel, according to physical laws, decreases in each nozzle by an amount multiple to the number of nozzles in the nozzle block. As a result, in each nozzle, respectively, the flow rate of the combustion products of solid fuel decreases and, as a result, the specific impulse (specific thrust) of the rocket engine decreases.

The technical result of the invention is a significant increase in the specific impulse of the rocket engine without significant complication of its design.

This technical result is achieved by the fact that in a rocket engine of solid fuel, comprising a housing with a front Bottom, an igniter and a solid fuel charge in the form of a cylindrical body with a central channel, housed in a housing, in the back of which is installed a multi-spun block, according to the invention, the solid fuel charge is equipped with peripheral through channels, the ends of a solid propellant charge are armored with diaphragms made of non-combustible material with low thermal conductivity, through holes are made in the diaphragms, with nye channels with solid fuel charge and the multi-nozzle unit mounted without play relative to the aperture in the bottom of the rocket engine, the front bottom formed with a recess on the inner surface, whereby the peripheral channels communicate the solid charge.

The invention is illustrated by drawings.

FIG. 1 shows the proposed rocket engine, general view, section. FIG. 2 is a section A-A in FIG. one; in fig. 3 is a section BB in FIG. one.

Rocket engine solid fuel contains a housing 1 of a cylindrical shape. A front plate 2 is installed in the front part of the housing 1, and a nozzle unit 3 with nozzles 4 is fixed in the lower part of the housing 1. Inside the housing 1 there is a solid-fuel charge 5 of cylindrical shape with a central channel 6 and peripheral channels 7. The central channel 6 is designed as a deaf axisymmetric holes, and the peripheral channels 7 are made in the form of through axisymmetric holes. The end parts of the solid-fuel charge 5 are armored front 8 and rear 9 diaphragms. In the diaphragms 8 and 9 are made through holes located coaxially with channels 6 and 7 in the solid-fuel charge 5. The nozzle unit 3 is installed in the housing 1 without a gap in relation to the diaphragm 9, and the nozzles 4 are installed coaxially with channels 6 and 7. Apertures 8 and 9 made of non-combustible material with low thermal conductivity, for example, asbestos or similar material. In the front bottom 2 on the inner surface there is a recess 10, for example, in the form of an annular groove. The recess 10 provides a physical connection (communication) between the channels 7 of the solid fuel charge 5 to equalize the pressure in the channels 7 when solid fuel is burning, which eliminates the occurrence of overturning moment due to the difference in thrust in the various nozzles of the multi-coil block 3. Igniters are installed in it 11, which turn on synchronously during the launch (launch) of the rocket.

The rocket engine works as follows.

After ignition of the fuel charge 5 by means of the synchronous actuation of the igniters 11, the gas flows of products of combustion of solid fuel from channels 6 and 7 enter the corresponding nozzles 4 of the multi-nozzle block 3. Due to the deepening 9 in the front bottom, pressure equalization is achieved and, as a result, the volumes and speeds are equalized the outflow of combustion products through the peripheral nozzles 4 of the multi-nozzle unit 3. The reservation of a solid fuel charge 5 with diaphragms 8 and 9 ensures the absence of mixing of product streams Oren between adjacent channels 7 and the nozzle 4. Thus is eliminated the decrease of pressure in the nozzles 4.

Thus, in essence, each individual channel 7 of a solid-fuel charge 5, together with a separate nozzle 4 coaxial with it, is an independent rocket engine, and the combination of all channels 7 and nozzles 4, simultaneously working, is a single engine in one case 1 with a single solid-fuel charge 5.

This allows you to repeatedly increase the specific impulse (specific thrust) without significantly complicating the design of the rocket engine, which, as a result, improves the tactical and technical characteristics of missiles using the proposed rocket engine.

Claims (1)

Rocket engine of solid fuel, comprising a housing with a front bottom, an igniter and a solid fuel charge in the form of a cylindrical body with a central channel, housed in a housing, in the back of which a multi-nozzle unit is installed, characterized in that the solid fuel charge is provided with peripheral through channels, the ends of the solid fuel charge are armored diaphragms are made of non-combustible material with low thermal conductivity, through holes are made in the diaphragms, coaxial with channels of solid fuel charge and nozzles are many oplovogo unit mounted without play relative to the aperture in the bottom of the rocket engine, the front bottom formed with a recess on the inner surface, whereby the peripheral channels communicate the solid charge.

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