Aktsionernoe obshchestvo "Cheboksarskoe proizvodstvennoe obedinenie imeni V.I. Chapaeva"
发明人:
Livshits Aleksandr Borisovich,Лившиц Александр Борисович,Mingazov Azat Shamilovich,Мингазов Азат Шамилович,Ponosov Vladimir Stepanovich,Поносов Владимир Степанович,Kashin Valentin Fedorovich,Кашин Вал
申请号：
RU2016124045
公开号：
RU0002620694C1
申请日:
2016.06.16
申请国别(地区):
RU
年份:
2017
代理人:
摘要：
FIELD: blasting.SUBSTANCE: rocket includes sequentially mounted takeoff and propulsion engines. There is an electric spark igniter fixed in the nozzle cluster of the takeoff engine with aerodynamic blades of the stabiliser. The igniter is associated with the launcher. In the case of the takeoff engine a channel powder charge, a pyrotechnic retarder for correcting the angle of the rocket flight and a collector of ignition of the propulsion engine with retarders for triggering the self-destruction belt charge of the takeoff engine are sequentially installed. By means of a dock adapter, the takeoff engine is connected to the propulsion engine, which has its own nozzle cluster and stabiliser in its design. The charge of the pyrotechnic propellant of the end combustion of the propulsion engine is at the same time an ice-forming stick of active smoke. The splitting grate located in the casing of the propulsion engine between the nozzle cluster and the pyrotechnic charge of the ice-forming pyrotechnic propellant of the end combustion allows one to collect the slags of the combustion products of the propellant and unburned particles, preventing slagging of the nozzle cluster. The consecutively located cumulative central destruction charge of the propulsion engine with the help of a detonator capsule provides the possibility of triggering the detonation and self-destruction of the propulsion engine. The rocket fairing is filled with an inert composition.EFFECT: increased yield of ice-forming nuclei from one gram of pyrotechnic propellant and missile range.3 cl, 1 dwgИзобретение относится к устройствам для изменения атмосферных условий и может быть использовано для рассеивания в облаках аэрозоля, генерируемого пиротехническим топливом, для предотвращения градобитий или искусственного вызывания осадков. Технический результат - увеличение выхода льдообразующих ядер с одного грамма пиротехнического топлива и дальности полета ракеты. Ракета включает последовательно смонтированные
