CZ335895A3 - Disposal method of rocket engines with a solid fuel - Google Patents

Abstract

Solid propellant rocket engines disposal ammonium perchlorate it consists in being on the surface of the inner channel element of solid fuel continuous layer of non-flammable substance and uninsulated the face of the solid propellant element to the bottom cover (bottom) of the rocket engine s the nozzle ignites. After ignition in space uninsulated front element rigid propulsion mass burns off controlled by "cigarette burning".

Description

The present invention relates to a process for the disposal of solid propellant rocket engines comprising ammonium perchlorate.

BACKGROUND OF THE INVENTION

Rocket engines for strategic missiles reach tens to hundreds of tons. To achieve the desired rocket acceleration, the engine must exert a thrust several times the mass of the entire rocket system. Achieving this necessary pressure is conditioned by the possibility of generating a large amount of gases, which form a substantial part of the combustion products of the solid fuel, in a very short period of time. This possibility is due not only to the chemical composition of the solid fuel, but also to the shape of the solid fuel element, which ensures a constant burn-off surface throughout the engine operation. The most commonly used solid rocket fuel is a heterogeneous mixture of chemicals containing ammonium perchlorate as the main constituent with other supplementary constituents (powdered aluminum, metal hydrides, hexogen, etc.). stars. The outer cylindrical surface of the solid fuel element, in some cases including both faces of the solid fuel element, is provided with an insulation against combustion. coating of non-combustible material. The inner non-insulated surface of the inner channel of the solid fuel element after ignition of the rocket engine guarantees optimum conditions of maximum fast and even combustion.

In many cases, obsolete or unusable rocket systems, including solid propellant rocket engines, need to be destroyed. So far, the destruction of rocket engines was carried out by igniting the stend or destruction using explosive charges. Both of these methods are absolutely undesirable especially from an ecological point of view, since in addition to a number of substantially environmentally harmless substances (such as nitrogen, carbon dioxide, alumina in the form of aerosols, etc.), a number of environmentally harmful and dangerous substances are always present. hydrogen chloride escaping into the atmosphere during these disposal operations. The capture and disposal of combustion products is impossible in such huge volumes when it is spilled. For these reasons, the disposal of discarded rocket engines with solid fuel elements was carried out in very remote locations, especially in deserts, and at long intervals necessary to disperse the combustion products into the atmosphere and the terrain.

Other more environmentally acceptable rocket engine disposal techniques are that large solid fuel elements are shredded or disintegrated into smaller parts, which are then burned in special plants or water-soluble substances are extracted from them. The separated insoluble substances are then destroyed in special equipment.

However, these described technologies are very demanding, costly and time-consuming at the stage of cutting or disintegration.

SUMMARY OF THE INVENTION

The aforementioned drawbacks are eliminated by the method of disposal of rocket engines with ammonium perchlorate-containing solid propellant elements, the outer surface of which, in addition to the face of the solid propellant element adjacent to the lower lid of the rocket motor with nozzle, is insulated against burning. The solid fuel element is insulated against combustion, after which the solid fuel element is ignited after the rocket engine has been closed in the non-insulated front space. The solid fuel element burns out at the front by cigarette burning practically at atmospheric pressure.

The main advantage of the ammonium perchlorate-containing solid propellant rocket engine disposal method of the present invention is that the burnout time of the solid propellant element is significantly prolonged, resulting in the combustion of combustion products over a substantially longer period of time, thereby enabling the selection of suitable technology and Capacitate equipment to capture these products and then dispose of them, eg by absorption, neutralization, etc.

It is particularly advantageous to carry out the destruction of the rocket motors by the method according to the invention below the water level or below the level of the neutralization solution with a pH higher than 7.

In some types of rocket engines, the elements are insulated over the entire outer surface, including both faces of the elements. In these cases, the surface of the inner channel of the solid fuel element is first insulated against combustion and subsequently removed

(removes) insulation against combustion from the front of the material adjacent to the lower nozzle lid. element stiff (in) missile propulsion engine Exemplary embodiment At the rocket engine it will be removed lower lid with nozzle

rocket engine, thereby allowing access to the inner channel of the cylindrical solid fuel element. The outer surface of the cylindrical portion of the solid fuel element is insulated from burning. Λ *

Both faces of the solid fuel element are also insulated from burning. An epoxy resin is applied in three layers to the inner surface of the six-pointed duct, which after curing adheres perfectly to the solid fuel and forms a continuous, non-flammable coating over the entire inner duct surface of the solid fuel element. Then, the insulating coating is removed from the front of the solid fuel element facing the rocket engine nozzle and the lower cap of the rocket engine nozzle is attached. The rocket engine thus prepared is stored and mounted on a stationary structure. After mounting the rocket engine, solid fuel at the non-insulated front ignites.

The burning time of the modified solid fuel element in the rocket engine is more than three hundred times longer than the original burning time of the solid fuel element, and it is technically possible to capture the combustion products and then dispose of them.

Industrial applicability

The method of disposing of solid propellant rocket engines comprising ammonium perchlorate according to the present invention is fully applicable to the destruction of discarded, unnecessary and outdated rocket technology.

Claims (1)

A method of disposing of solid propellant rocket engines comprising ammonium perchlorate, the outer surface of which, in addition to the front face of the solid propellant adjacent to the lower cap of the rocket engine with nozzle _x, is insulated against burning, burnout, characterized in The fuel element is insulated against combustion, after which the solid fuel element is ignited after the rocket engine has been closed in the non-insulated front face.