Installation for reclamation of propellant charges of small-size rocket engines

FIELD: rocketry.

SUBSTANCE: proposed installation contains accumulating reservoir, dust trap and adsorber, all connected with engine nozzle by gas lines and arranged in technological sequence. Dust trap is made in form of hermetically sealed chamber provided with upper and lower rows of plates arranged at tilting at equal angle. Plates of upper and lower rows alternate, and their outer edges overlap each other. Coarse and fine filters are installed between dust trap and adsorber. Said filters made in one housing are arranged on wire skeleton. Adsorber is made in form of vertical cylinder whose lower part is filled with crushed stone, and upper part, with activated charcoal.

EFFECT: provision of ecologically safe combustion of solid-propellant charges of small-size rocket engine in the air.

4 dwg

 

The invention relates to mechanical engineering and can be used for testing solid rocket motor, ensuring environmental safety requirements.

Testing of solid propellant rocket motors, and their destruction upon the expiration of exploitation is a serious problem because of the danger of environmental pollution by harmful combustion products.

Known various devices for safe burning of solid propellant rocket motors.

The device according to U.S. patent No. 6101957 proposes to use the secondary combustion chamber of a large volume, which expire products of combustion from solid rocket motor chamber.

These products are mixed with air and burning low, and the output nozzle has a multi-level path to turbulence in the flow.

Also known installations for the disposal of special-purpose motors missile systems in which gases after combustion of solid rocket motor first pass through the gas path with filler, and then arrive in a container that collects the condensate and gases, and then displayed on further purification and neutralization (Korepanov M.A. "Disposal of special-purpose motors missile systems", proceedings of the international seminar “Scientific-technical potential of the Western Urals military-industrial complex” 17-27 June 2001, Perm, Russia, p.67-68).

This installation is essential if Nakov is closest to the claimed.

The disadvantages of this setup are incomplete purification of products of combustion from solid particles and oxides and the necessity of releasing the capacity of the disk drive after each test.

The technical task of the present invention is to remedy these disadvantages.

The technical result is achieved in that the apparatus for disposing of fuel charges small rocket engines containing gotowanie with the nozzle of the engine and located in the technological sequence of cumulative capacity, dust-separating device, the adsorber, the dust catching device is designed as a sealed chamber in which is placed the upper and lower rows of obliquely arranged at the same angle plates, while the plates of the upper and lower rows are interleaved, and their outer edges overlap between the dust collecting device and adsorber filters are coarse and fine cleaning, made in one case and placed on a wire frame, and the adsorber is made in the form vertical cylinder, the bottom of which is filled with rubble, and the upper activated carbon.

Figure 1 presents a functional diagram of the installation.

Figure 2 - design of the dust collecting device.

Figure 3 - design of coarse and fine filter.

On Fig - the design of the adsorber.

In figure 1, 2, 3, 4 indicated:

1 - compact rocket engine

2 - capacity

3 - regulating device

4 - dust device

5 - layer filter

6 - adsorber

7 - plate top row dust collecting device

8 - plate of the bottom row dust collecting device

9 - fiberglass

10 - material FRR-15 (Petryanov filter material)

11 - gravel

12 - charcoal

The device operates as follows:

The combustion products of solid rocket motor (1) are cumulative capacity (2), in which, expanding, they are cooled to a temperature of ≈150°C. the most heavy particle size >100 μm remain in the tank. Then, after passing the regulating device (3), the products of combustion come in the dust catching device (4), in which through the labyrinth formed by the outer portions of the top plates (7) and bottom row (8), onto a particle size of >50 microns. The remaining products of combustion enters the two-layer filter (5), passing successively rough treatment in fiberglass (9) and thin clearance through the material FRR-15 (10), which captures the remaining solid particles. The gas phase, the main component of which is the SO2after the filter enters the adsorber (6), in which, after the placenta is therefore a layer of crushed stone (11), and then a layer of activated charcoal (12)emitted into the atmosphere as carbon dioxide, and the resulting N2SO4+H2Oh come on cleanup.

Using the setup allows to ensure the environmentally safe testing and burning small solid rocket motor.

Economic efficiency is to prevent environmental damage from burning solid-propellant charges in the open air.

Installations for the disposal of fuel charges small rocket engines containing gotowanie with the nozzle of the engine and located in the technological sequence of cumulative capacity, dust-separating device, the adsorber, wherein the dust-collecting device is mounted in a sealed chamber in which is placed the upper and lower rows of obliquely arranged at the same angle plates, while the plates of the upper and lower rows are interleaved, and their outer edges overlap between the dust collecting device and adsorber filters are coarse and fine cleaning, made in one case and placed on a wire frame, and the adsorber is made in the form of a vertical cylinder, the lower part of which is filled with rubble, and the upper activated carbon.



 

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