FIELD: aviation.
SUBSTANCE: in order to destroy the parts of waste spacecraft by perforating the high-heat structural material of the spacecraft components when it falls in dense atmosphere, a pyrotechnic composition of thermite type, based on aluminium and metal oxide, capable of self-ignition at a temperature of 900-1000°C and with an exothermic effect of at least 4200 kJ/kg, is applied to the surface of the spacecraft parts. The pyrotechnic composition of thermite type is filled in a cylindrical nozzle made of titanium alloy, which is fixed on the surface of spacecraft parts. To ensure the compression of the pyrotechnic composition to the surface of the material, an elastic heat-insulating liner is installed inside the cylindrical nozzle.
EFFECT: method and device provide high safety, stability and reliability and allow perforating the high-heat parts of waste spacecrafts at the stage of their uncontrolled descent in dense atmosphere.
6 cl, 4 dwg, 1 tbl
Title | Year | Author | Number |
---|---|---|---|
METHOD FOR MINIMIZATION OF EXCLUSION ZONES FOR CARRIER ROCKET SEPARATING PARTS AND DEVICE FOR ITS IMPLEMENTATION | 2018 |
|
RU2700150C1 |
PROCEDURE BY VOLKOV FOR PRODUCTION OF CHEMICALLY ACTIVE METALS AND DEVICE FOR IMPLEMENTATION OF THIS PROCEDURE | 2008 |
|
RU2401874C2 |
PYROTECHNIC COMPOSITION CREATING INFRARED RADIATION | 2023 |
|
RU2819727C1 |
NANOCHEMICAL METHOD OF COMPOSITE MATERIALS FABRICATION | 2007 |
|
RU2347647C1 |
METHOD OF ALUMINO-THERMAL PRODUCTION OF FERRO-TITANIUM | 2006 |
|
RU2338805C2 |
HEATPROOF COMPOSITION POWDER ALLOY ON BASIS OF INTERMETALLIC SEMICONDUCTOR NiAl AND METHOD OF ITS RECEIVING | 2008 |
|
RU2371496C1 |
METHOD OF PRODUCING ALLOYED METAL | 0 |
|
SU1232440A1 |
METHOD OF MINIMIZING ZONES OF DETACHABLE PARTS EXCLUSION OF CARRIER ROCKET | 2015 |
|
RU2626797C2 |
CHARGE OF STAROVEROV - 9 (VERSIONS) | 2012 |
|
RU2485434C1 |
MISSILE NOSE CONE | 2015 |
|
RU2581636C1 |
Authors
Dates
2017-11-29—Published
2016-04-14—Filed