RU2267025C2 - Solid-propellant rocket engine test set - Google Patents

Abstract

FIELD: rocketry; test facilities.

SUBSTANCE: proposed test set designed for testing small-size solid propellant rocket engines contains storage reservoir and combustion products cleaning system interconnected by gas-dynamic duct. Storage reservoir is installed directly after engine and is hermetically connected with engine nozzle. Gas cooler is installed in gas-dynamic duct between storage reservoir and cleaning system.

EFFECT: no adverse action on environment at combustion of solid propellant charge in the open.

1 dwg

Description

The invention relates to mechanical engineering and can be used in the manufacture of equipment for testing solid propellant rocket engines (solid propellant rocket engines), as well as burning fuel in the process of their disposal, ensuring environmental safety requirements.

Tests of solid propellant solid propellants, as well as their disposal associated with the burning of fuels, after the expiration of their service life, present a serious problem because of the danger of environmental pollution by harmful combustion products.

A device for the safe combustion of solid propellant solid propellants is known from patent information sources (see US Pat. No. 6,101,957). The device comprises a large-scale afterburner, into which combustion products from the solid propellant chamber enter. In the afterburner, the combustion products are mixed with air, burn out and expire into the atmosphere, passing through an outlet nozzle having a multi-stage circuit for turbulizing the flow.

There is also an installation for the disposal of special-purpose engines of rocket complexes, in which gases after burning solid propellant rocket pass first through a gas-dynamic path with a filler, and then enter a tank in which condensate and gases are collected and then removed for further purification and neutralization (see theses reports of MA Korepanova and others. “Utilization of special-purpose engines of missile systems” published in the collection of reports of the international seminar “Scientific and technical potential of the military-industrial a complex of the Western Urals "17-27 June 2001 Perm, Russia UDC 576.8: 621: 6285: 660).

In terms of combination of features, the installation is closest to the claimed one.

A disadvantage of the known installation is the incomplete purification of combustion products from solid particles and oxides due to the composition of the gas-air mixture that is not optimal in temperature and particle size for the filtering materials of the cleaning system, as well as in the absence of requirements for the location of the solid propellant rocket engine (up to the storage tank or inside it), which, under conditions of placing the engine inside the storage tank, can lead to the destruction of the engine due to the influence of thermal and dynamic loads arising inside the storage tank d capacity from the running engine.

An object of the present invention is to remedy this drawback.

The technical result is achieved by the fact that in the installation for testing rocket engines containing a storage tank and a system for cleaning combustion products connected by a gas dynamic path, the storage tank is installed directly after the engine and is hermetically connected to its nozzle, while in the gas dynamic path, between the storage tank and a gas cooler is installed in the cleaning system.

The drawing shows a functional diagram of the installation, on which are indicated:

1 - rocket engine;

2 - storage capacity;

3 - gas-dynamic path;

4 - gas cooler;

5 - cleaning system.

The installation works as follows: the combustion products from the solid propellant solid fuel (1) enter the storage tank (2), in which, expanding, they are cooled to a temperature of ~ 150 ° C. In this case, the heaviest particles larger than 100 microns remain in the container from which they are periodically removed and sent to the landfill for disposal. Further, the combustion products through the gas-dynamic path (3) enter the gas cooler (4), where the temperature of the gas-air mixture decreases at a rate of 2 · 10 ⁴ k / s for 0.01 s, which leads to the formation of particles with an average size of 0.07 μm and thereby completes the formation of ultrafine particles of combustion products, i.e. the optimal composition of the gas-air mixture is formed in terms of temperature and particle size, which ensures effective cleaning by filtering materials of the cleaning system (5).

The placement of solid propellant rocket motors in conditions outside the storage tank increases the safety of work.

Using the facility allows for environmentally friendly testing and combustion of solid propellant rocket motors.

The economic efficiency of the invention is to prevent environmental damage from the burning of solid propellant rocket charges in the open.

Claims (1)

Installation for testing small-sized rocket engines of solid fuel (RDTT), containing a storage tank and a system for cleaning combustion products connected by a gas-dynamic path, characterized in that the storage tank is installed directly after the engine and is hermetically connected to its nozzle, while in the gas-dynamic path between a gas cooler is installed in the storage tank and purification system.