发明名称 LIQUID-PROPELLANT ROCKET ENGINE CHAMBER LOCK
摘要 FIELD: engines and pumps.SUBSTANCE: proposed lock comprises adjusting pyrotechnic retainer and adjustable link arranged between the chamber and engine frame. Lug is secured at combustion chamber cylindrical part while plate with pads is fitted between rods and frame base. Holes are made at said lug and pads for adjusting retainer and pyrotechnic retainer to be fitted therein. Bracket and cramp with links with holes are welded to combustion chamber cylindrical part and frame, adjusting drawbar secured by pins in links holes being arranged there between. Adjusting retainer secured at frame plate pad has one conical surface in contact with mating conical surface in pad hole and another conical guide surface at the retainer opposite side.EFFECT: integrity of engine chambers at transportation, higher reliability of locking at engine ground tests, chamber unlocking at carrier rocket flight initial path.5 cl, 15 dwg
申请公布号 RU2530364(C1) 申请公布日期 2014.10.10
申请号 RU20130113535 申请日期 2013.03.26
申请人 OTKRYTOE AKTSIONERNOE OBSHCHESTVO "KONSTRUKTORSKOE BJURO KHIMAVTOMATIKI" 发明人 GOL'BA ANATOLIJ VIKTOROVICH;KUZNETSOV ALEKSANDR VASIL'EVICH;RAD'KO DMITRIJ VLADIMIROVICH;TURTUSHOV VALERIJ ANDREEVICH
分类号 F16B2/20 主分类号 F16B2/20
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