METHOD FOR ELIMINATION OF CHARGE OF LARGE-SIZED SOLID-PROPELLANT ROCKET ENGINE WITHOUT NOZZLE UNIT BY COMBUSTION METHOD Russian patent published in 2007 - IPC F42B33/00 

FIELD: elimination of charges of large-sized rocket engines without nozzle units on open and closed stands with gas purifying systems.

SUBSTANCE: the method offers introduction of a fuel charge in the central channels of the sectionalized nozzle packing, whose sections are coupled by two pipe lines on the side of the front bottom to the systems of separate feed of neutralizing and cooling aqueous solutions. An aqueous solution of sodium, potassium and calcium nitrates in a mixture with oxidants-ammonium nitrate and/or nitric acid is used as the neutralizing solution, which is fed by a hydraulic giant to the flow core of the combustion products through the central section of the nozzle packing with a flow rate of 1.01 to 1.2 of the rated flow rate of the combustion products. An aqueous solution of polyacrylamide and/or its copolymers is used as the cooling solution, it is fed by a hydraulic giant to the peripheral sections of the nozzle packing with a floorate providing for monitoring of propagation of the flame front on the surface of the charge channel and cooling of the exposing inner walls of the rocket engine body. Adjustment of the hydrodynamic characteristics of the nozzle packing is performed by supply of alternating current from the ultrasonic generator to the radiators installed in the sectionalized nozzle packing. The longitudinal, transverse slots and a portion of the central channel of the large-sized charge from the front bottom to the plane of installation of the sectionalized nozzle packing are filled in by a solidified polyacrylamide gel.

EFFECT: enhanced explosion proofness of the combustion process on closed stands-equipped with gas purifying systems, provided high, ecological requirements to the composition of the gas and aerosol effluents at an expansion of the list of probable defects of the charges of large-sized engines allowed to elimination by the combustion method with a simultaneous provision of the safety of the solid-propellant rocket engine body after elimination of its charge.

5 cl, 1 dwg