RU2260143C2 - Solid-propellant gas generator - Google Patents

Abstract

FIELD: rocket catapult.

SUBSTANCE: proposed solid-propellant gas generator for rocket catapult launcher has housing with front cover, support grill, pyrotechnical cartridge and granulated solid fuel charge. Said charge is placed in sealed sectional envelope of polymeric film in form of cartridge carrier turned into cylinder with central channel and adjoining inner surface of housing. Partially perforated tube-igniter fitted in central channel is connected with front cover of gas generator and support grill. Perforated section of tube-igniter adjoins support grill, being equal to 1/5-1/4 of its length. Pyrotechnical cartridge is installed in front cover and is hydrodynamically coupled with tube-igniter. Sections of cartridge carrier are made to full length of combustion chamber of gas generator housing.

EFFECT: provision of effective launching of rocket from launch tube at minimum action onto gas generator.

12 cl, 2 dwg

Description

The invention relates to the field of rocket technology and can be used in the design, development and manufacture of solid fuel gas generators (GG), in particular for ejection systems of rockets and other devices.

One of the main features of ejection devices is the burning of their solid propellant charges in a variable expanding volume. This requires the development of special designs of charges and schemes of their ignition, providing, on the one hand, reliable ignition of the charge, and on the other, the acceptable nature of the pressure-time relationship P (τ), which guarantees both the necessary level of forces transmitted to the catapult mass and providing working conditions (non-destruction) of the gas generator and the ejection device as a whole.

For this purpose, it is desirable to realize the most uniform, close to neutral, pressure-time curve in the “projectile space” of the ejection mass.

In analogs (DE 2028539 B2, FR 2623249 A1, DE 2605768 A1, DE 2623581 A1, DE 2757764 A1, DE 2912874 A1, J. "Science and Technology", No. 10, 2001, pp. 2-6, 10-12) This problem is mainly solved by using multi-cup channel charges in gas generators (squibs), which makes it possible to implement a progressive combustion law and partially compensate for thermal and gas-dynamic losses in an expanding volume. The disadvantage of analogues is the complex, labor-intensive construction of solid propellant charges.

The closest analogue of the patented fuel gas generator is the invention according to US Pat. RU 2213245, coinciding with it for most of the similar features, adopted by the authors as a prototype. The disadvantage of the prototype is the low operational efficiency of the charge structure in the gas generator, in terms of the absence (impossibility) of conditions for the implementation of a time-programmed charge response and a progressive pressure-time curve.

The technical task of the patented invention is to develop a gas generator design with a solid fuel charge that provides a reliable start from the rocket ejection launcher and permissible (acceptable) loads, primarily by pressure in the GG chamber, on the generator design and rocket launch ejection device, as well as the possibility of programming dependencies ″ pressure-time ″ and compactness of the device.

The technical result of the invention is achieved by equipping a solid fuel gas generator containing a combustion chamber and a front cover with a sectional charge of granular solid fuel, made in the form of a sealed sectional shell (bandoleer) from a polymer film rolled into a cylinder with a central channel, with each shell section being filled solid fuel until it is tightly packed, and the rolled-up shell (bandoleer) is adjacent to the inner surface of the gas generator housing without a gap. At the same time, a partially perforated ignition tube is mounted inside the channel, fastened to the front cover of the hot gas cylinder and tightly or with a throttling hole - with a support grid, and in the area adjacent to the support grill (at a length of 1/5 ... 1/4 from the grill ), the pilot tube is perforated with radial holes. Openings for passing gases to the GG consumable block are made in the support grid. In this case, the pyro cartridge is located on the front cover side, and the solid fuel charge is made in the form of sections filled with smoky gunpowder (DRP), including coarse smoky gunpowder (KZDP), or ballistic rocket fuel granules, or a mixture of DRP and KZDP of various dispersion, or a mixture of pellets of ballistic rocket fuel and smoky gunpowder, or a mixture of DRP-2 and KZDP-2 powder in a ratio of 1: 8 ... 1:10, and each section of the charge shell is made with tight packing for the entire length of the combustion chamber (body) gas generator pa. As the material of the polymer film, polyethylene terephthalate laminated with polyethylene is used.

The design of the patented solid fuel gzogenerator and the scheme of its use in the ejection system are shown in figure 1, figure 2.

FIG. 1. Design patentable GG:

1 - ignition tube;

2 - front cover;

3 - throttling hole;

4 - a support lattice;

5 - radial holes;

6 - holes in the support grid;

7 - a squib;

8 - solid fuel charge sections;

9 - combustion chamber.

Figure 2. Layout of the GG in the missile launch block:

10 - gas generator (GG);

11 - a rocket;

12 - launch tube.

When a pulse is applied (Fig. 1) to the igniter (7), the latter detonates and the igniter gases move to the nozzle tip of the igniter tube (1) and enter the solid fuel charge sections (8) through perforated radial holes (5), initially igniting the nozzle part of the charge . The gases of the pyro cartridge and the charge flammable under their influence propagate through the gaps between the pilot tube and the charge both towards the front bottom (2) and to the support grid (4) with a certain time delay (due to thermal and gas-dynamic losses during gas movement in gaps and the specific time required to melt the polymer film). Due to the close packing of the sample in sections of the solid fuel charge, it burns out by a mechanism close to the burning of monoblock solid fuel checkers, that is, it is quite monotonous, and not immediately throughout the charge volume. This contributes to the perforation of the radial holes of the pilot tube, with a length of at least 1/5 of its length from the support grid (guaranteeing reliable ignition of the charge) and no more than 1/4 of the length, which allows for monotonous (“time-stretched”) charge burning. The noted technical features of the GG make it possible to coordinate the gas intake from the GG (Fig. 2) with an expanding variable volume between the GG (10) and the ejected rocket (11) in the vertical launch block (pipe) (12) and provide, with an acceptable level of pressure in the combustion chamber of the gas generator effective shooting of the ejected mass of the rocket.

The technical effect of the patented invention is achieved by:

- installation of the igniter tube in the central channel of the charge shell (bandoleer) rolled into the tube;

- execution of the igniter tube over the length of the combustion chamber from the front cover to the support grill and either muffled on the support grill or with a throttling hole (3) for partial discharge of combustion products directly from the igniter to the GG consumable block;

- perform perforation at the tip of the pilot tube adjacent to the support grid, at a length of 1/5 ... 1/4 of the grid;

- placing the squib inside or outside the pilot tube from the front bottom;

- use as solid fuel a granular sample of smoky gunpowder or ballistic fuel, moreover, to ensure tight packaging, a combined sample can be used that includes both smoke gunpowder and ballistic of various particle sizes;

- use as the material of the shell charge polyethylene terephthalate film laminated with polyethylene.

Patented design is implemented for an ejection rocket system with the following launch launch parameters:

- steel casing with overall dimensions: length 300 mm, diameter 70 mm;

- KZPD-1 charge-powder weighing 480 ... 550 grams, placed in three sections of a bandoleer from a polymer film;

- ignition tube: diameter 10 mm with 16 holes 5 mm in diameter, located at ~ 1/4 of the length from the support grid;

- squib.

Claims (11)

1. A solid fuel gas generator for a rocket ejection device, comprising a housing with a front cover, a support grill, a squib and a charge of granular solid fuel placed in a sealed sectional shell made of a polymer film in the form of a cartridge belt rolled into a cylinder with a central channel, with each section of the bandoleer filled with solid fuel until it is tightly packed, and the rolled bandolier is adjacent to the inner surface of the housing, characterized in that a partially perforated one is installed in the central channel ignition tube bonded to the front cover of the gas generator and the support grill, while the perforated portion of the ignition tube is adjacent to the support grill and is 1/5 ... 1/4 of its length from the grill, and the igniter is installed in the front cover providing gas-dynamic communication with a pilot tube, and the cartridge band sections are made to the full length of the combustion chamber of the gas generator housing. 2. Solid fuel gas generator according to claim 1, characterized in that the solid fuel used smoky gun powder. 3. The solid fuel gas generator according to claim 2, characterized in that a mixture of smoky gunpowder of various dispersion is used as solid fuel. 4. The solid fuel gas generator according to claim 3, characterized in that a mixture of smoky gunpowder DRP-2 and KZDP-2 in a ratio of 1: 8 ... 10 is used as solid fuel. 5. The solid fuel gas generator according to claim 2, characterized in that a mixture of smoky gunpowder DRP-2 and KZDP-2 in a ratio of 1: 8 ... 10 is used as solid fuel. 6. The solid fuel gas generator according to claim 1, characterized in that granules of ballistic rocket fuel are used as solid fuel. 7. The solid fuel gas generator according to claim 1, characterized in that a mixture of granules of ballistic rocket fuel and smoke gun powder is used as solid fuel. 8. The solid fuel gas generator according to claim 1, characterized in that a mixture of smoky gunpowder of various dispersion is used as solid fuel. 9. The solid fuel gas generator according to claim 8, characterized in that a mixture of smoky gunpowder DRP-2 and KZDP-2 in a ratio of 1: 8 ... 10 is used as solid fuel. 10. The solid fuel gas generator according to claim 1, characterized in that a mixture of smoky gunpowder DRP-2 and KZDP-2 in a ratio of 1: 8 ... 10 is used as solid fuel. 11. A solid fuel gas generator according to any one of claims 1 to 10, characterized in that the charge shell is made of a polyethylene terephthalate film laminated with polyethylene, and the ignition tube is plugged from the side of the support grid, in which a throttling hole is made.

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